JP4764474B2 - gas turbine - Google Patents

Description

The present invention relates to a gas turbine, and in particular, to an improvement in the structure of a joint portion between a tail blade of a combustor and a stationary blade shroud.

A gap for releasing thermal expansion is provided between the rear end (downstream end) of the combustor of the gas turbine combustor and the stationary blade shroud of the first stage stationary blade of the turbine.

However, this gap can also be a path for combustion gas to leak out of the gas flow path. Leakage of combustion gas from the gas flow path must be prevented because combustion gas leaks out of the gas flow path and causes gas turbine burnout.

In general gas turbines, the following two methods are employed to prevent leakage of combustion gas from the gas flow path. One is to make the pressure of the compressed air in the passenger compartment (that is, the pressure outside the gas passage) higher than the pressure in the gas passage. By making the pressure in the passenger compartment higher than the pressure in the gas flow path, the fuel gas can be prevented from leaking out of the gas flow path. Another approach is to provide a seal in the gap. By providing a seal in the gap,
The path through which the combustion gas leaks is narrow, and combustion gas leakage can be suppressed. Providing a seal in the gap is also important for reducing the amount of compressed air flowing into the gas flow path. If the gap is left without a seal, a lot of compressed air flows into the gas flow path. This is not preferable because it reduces the performance of the gas turbine. In a gas turbine that employs both of these methods, the state in which compressed air slightly flows out into the gas flow path is maintained from the gap between the seal and the tail cylinder and the gap between the seal and the stationary blade shroud. As a result, leakage of combustion gas from the gas flow path is prevented.

As the structure of the seal provided in the gap, two types of structures are known.
One is a structure in which the seal faces the combustion gas flow path (see FIG. 1 of JP 2000-257862 A and FIG. 1C of JP 2001-289003 A). FIG.
The structure of the seal | sticker currently disclosed by 01-289003 is shown. In the structure of FIG. 1, a seal 104 is provided in the gap between the rear end of the tail cylinder 101 and the stationary blade shroud 103 that supports the stationary blade 102. The combustion gas 105 is ejected from the rear end of the tail cylinder 101 to the stationary blade 102.

The other is a structure in which a seal is provided at a position away from the gas flow path (Japanese Patent Laid-Open No. 2001-2).
(See FIGS. 1A and 1B of the 89003 publication). 2A and 2B are disclosed in JP-A-2001-2.
The structure of the seal | sticker currently disclosed by 89003 is shown. In the structure of FIG. 2A, the rear end portion 101b of the tail cylinder 101 extends downstream from the flange 101a to which the seal 104 is connected. Such a structure prevents the seal 104 from being directly exposed to the combustion gas 105. As shown in FIG. 2B, the front end portion 103b of the stationary blade shroud 103 may be extended upstream from the flange 103a to which the seal 104 is connected.
This is effective to prevent 4 from being directly exposed to the combustion gas 105.

The advantage of the structure of FIGS. 2A and 2B over the structure of FIG. 1 is that the amount of cooling air that cools the seal may be small. In the structure of FIG. 1, the combustion gas 105 whose seal 104 is hot is used.
A large amount of cooling air 104a is supplied to the seal 104 for direct exposure to the seal 104.
Need to be cooled. The increase in cooling air 104a that cools the seal 104 creates the need to allocate more of the compressed air generated by the compressor to the cooling air 104a, increasing the burden on the compressor. This is not preferable because it reduces the performance of the gas turbine. 2A and 2B, since the seal 104 is not directly exposed to the high-temperature combustion gas 105, the cooling air 104a may be small. This is preferable for improving the performance of the gas turbine.

However, the structure proposed heretofore has a combustor tail cylinder 101 and a stationary blade shroud 1.
It is not perfect to protect the part of the gap between 03 and the combustion gas. This is because the pressure of the combustion gas is not uniform in the circumferential direction of the stationary blade row. 3 and 4 are diagrams for explaining the non-uniformity of the pressure of the combustion gas. When the combustion gas 105 is blown onto the stationary blade 102, as shown in FIG. 3, a stagnation point 102 with a high pressure is formed near the leading edge of the stationary blade 102.
a appears. In other words, as shown in FIG. 4, the pressure of the combustion gas 105 is high in the vicinity of the stagnation point 102 a and is low in the middle position between the stagnation points 102 a of the adjacent stationary blades 102. Such a pressure distribution generates a flow in which the combustion gas 105 flows between the rear end of the tail cylinder and the front end of the stationary blade shroud in the vicinity of the stagnation point 102a, and compressed air is ejected at a position intermediate the stagnation point 102a. Let This can cause burning in the gap between the rear end of the combustor tail and the front end of the vane shroud.

The incomparability of the pressure of the combustion gas is a problem particularly in a structure in which a seal is provided at a position away from the gas flow path as shown in FIGS. 2A and 2B. The incomparability of the combustion gas pressure described above is due to the combustion into the cavity between the combustor's tail cylinder and vane shroud (ie, the space surrounded by the tail cylinder, seal and vane shroud). Invoke gas. This leads to burnout in the cavities, especially seal damage. In order to prevent damage to the seal, it is possible to supply a large amount of cooling air to the seal, but this loses the advantage of providing the seal at a position away from the gas flow path.

This effectively prevents burning of the gap between the rear end of the combustor tail and the front end of the vane shroud due to non-uniform combustion gas pressure in the circumferential direction of the stator blade row. It is extremely beneficial to provide technology for this purpose.
JP 2001-289003 A JP 2001-289003 A

An object of the present invention is to effectively prevent burning of a gap portion between a combustor tail cylinder and a stationary blade shroud due to non-uniformity of combustion gas pressure in the circumferential direction of the stationary blade row. Is to provide the technology.

In order to achieve the above object, the present invention employs the following means. In the description of technical matters constituting the means, in order to clarify the correspondence between the description of [Claims] and the description of [Best Mode for Carrying Out the Invention] Number / symbol used in the best mode for doing this is added. However, the added numbers and symbols shall not be used for the interpretation of the technical scope of the invention described in [Claims].

In one aspect, a gas turbine according to the present invention includes a combustor (3) that ejects combustion gas (3a) from a tail tube (4), and a turbine (3a) that is supplied with combustion gas (3a) from a tail tube (4). 5
7). The turbine (5-7) includes a stationary blade (5) and a stationary blade shroud (6) that is located downstream of the tail cylinder (4) and supports the stationary blade (5). At the downstream end (4a) of the transition piece (4), the cooling air (6a) toward the upstream end (6a) of the stationary blade shroud (6)
13) At least one opening (4c) for jetting is provided. Cooling air (1) from the downstream end (4a) of the transition piece (4) toward the upstream end (6a) of the stationary blade shroud (6)
3) By ejecting the gas, combustion gas into the gap between the tail cylinder (4) and the stationary blade shroud (6) (
The intrusion of 3a) is effectively prevented. Since supplying the cooling air to the end (4a) of the tail tube (4) is originally necessary for cooling the end (4a), even if the cooling air (13) is ejected, There is no additional consumption of compressed air (1a) produced by the compressor (1). This is suitable in order not to deteriorate the performance of the gas turbine due to an increase in the consumption of compressed air (1a).

From the downstream end (4a) of the transition piece (4) to the upstream end (6a) of the stationary blade shroud (6)
Instead of, or in addition to, blowing out the cooling air (13) toward the end, the upstream end (6a) of the stationary blade shroud (6) to the downstream end (4a) of the tail cylinder (4) Cooling air (14
). In this case, the upstream end (6a) of the stationary blade shroud (6)
) Is provided with at least one opening (6c) through which the cooling air (14) is ejected toward the downstream end (4a) of the transition piece (4).

The flow rate of the cooling air (13, 14) flowing into the gap between the downstream end (4a) of the transition piece (4) and the upstream end (6a) of the stationary blade shroud (6) It is preferable that (5) is not uniform in the direction in which the lines are arranged. More specifically, the opening (4c, 6c) of the tail blade (4) and / or the stationary blade shroud (6) is located upstream of the stagnation point (15) of the leading edge of the stationary blade (5) in the gap. It is preferable that the flow rate of the cooling air flowing into the gap is larger than the flow rate of the cooling air flowing into a position away from the upstream of the stagnation point (15) of the gap.

In order to realize this, the density of the opening (4c) of the tail tube (4) upstream of the stagnation point (15) is such that the density (4c) of the tail tube (4) at a position away from the stagnation point (15). It is preferable that the density is larger than the density. Further, the area of the opening (4c) of the tail tube (4) provided at the upstream position of the stagnation point (15) is equal to the opening of the tail tube (4) provided at a position away from the stagnation point (15) (
It is preferred that it is larger than the area of 4c).

In this case, in order to make the temperature of the transition piece (4) uniform, the combustor (3) and the stationary blade (5)
It is preferable that the temperature of the transition piece (4) at a position upstream of the stagnation point (15) is configured to be higher than that of other portions. More specifically, the combustor (3) preferably includes a combustion nozzle (19) at a position corresponding to the upstream of the stagnation point (15).

In order to increase the penetration force of the cooling air (13, 14) and to suppress the intrusion of the combustion gas (3a), the cooling air (13, 14) is moved to the opening of the tail cylinder (4) or the stationary blade shroud (6) ( 4c, 6b)
It is preferable that the cooling air passages (4b, 6b) to be supplied have a tapered shape toward the openings (4c, 6b).

Of the opening (4c) of the transition piece (4), the one provided upstream of the stagnation point (15) of the leading edge of the stationary blade (5) is the first opening (4c-1) and the stagnation point ( 15) is defined as a second opening (4c-2) provided at an intermediate position, and a cooling air passage for supplying cooling air to the first opening (4c-1) of the tail cylinder (4) is further defined as the first opening. When the cooling air passage (4b-1) and the cooling air passage for supplying the cooling air to the second opening (4c-2) are defined as the second cooling air passage (4b-2), the first cooling air passage (4b-1) The downstream end of -1) is inclined toward the surface of the transition piece (4) through which the combustion gas (3a) flows, and the downstream end of the second cooling air passage (4b-2) is Combustion gas (3) in the cylinder (4)
It is preferable to be inclined to the side opposite to the surface through which a) flows.

Similar techniques can be applied to the vane shroud (6). The downstream end of the first cooling air passage for supplying the cooling air to the first opening provided at the upstream position of the stagnation point (15) at the leading edge of the stationary blade (5) is a stationary blade shroud (6). The downstream end of the second cooling air passage that is inclined toward the surface through which the combustion gas (3a) flows and supplies cooling air to the second opening provided at a position intermediate the stagnation point (15) is: It is preferred that the vane shroud (6) be inclined to the side opposite to the surface.

The openings (4c, 6c) provided in the tail tube (4) or the stationary blade shroud (6)
It is also preferable that the slits are formed as long slits in the direction in which they are arranged. In this case, it is preferable that the cooling air passages (4b, 6b) for supplying the cooling air to the openings (4c, 6c) have a tapered shape toward the openings (4c, 6c). Also, the stagnation point (15
The width of the slit at a position upstream of () is preferably wider than the width of the slit at a position away from the position upstream of the stagnation point (15). Even in this case, it is preferable that the combustor (3) and the stationary blade (5) are configured such that the temperature of the transition piece (4) at a position upstream of the stagnation point (15) is higher than that of the other portions. It is. Specifically, the combustor (3) has a stagnation point (15).
It is preferable that the combustion nozzle (19) is provided at a position corresponding to the upstream side.
gas turbine.

In this case, the cross section of the cooling air passage (4b, 6b) for supplying the cooling air to the opening (4c, 6c) upstream of the stagnation point (15) at the leading edge of the stationary blade (5) is on the downstream side. A cooling air passage (4b) having an end inclined to the side through which the combustion gas (3a) flows, and supplying cooling air to the openings (4c, 6c) at positions away from the upstream of the stagnation point (15) , 6b) preferably has a shape inclined to the side opposite to the side through which the combustion gas (3a) flows.

Further, turbulent flow generating means (for generating turbulent flow in the cooling air in the second cooling air passage (4b-3) communicating with the second opening (4c-3) provided in the middle position of the stagnation point (15) ( It is also preferred that 16) is formed. In addition to the turbulent flow generation means (16), a first cooling air passage (4b-4) for supplying cooling air to a first opening (4c-4) provided upstream of the stagnation point (15)
Other turbulence generating means (17) for causing turbulence in the cooling air can be formed. In this case, the second
The turbulent flow generation means (16) provided in the cooling air passage (4b-3) is connected to the first cooling air passage (4
It is preferable that the cooling effect of the transition piece (4) is higher than that of the other turbulent flow generation means (16) provided in b-4).

The same applies to the case where the openings (4c, 6c) for ejecting the cooling air are formed in a slit shape that is long in the direction in which the stationary blades (5) are arranged. Turbulent flow generating means (18) for causing turbulent flow in the cooling air in the slit-shaped cooling air passages (4b, 6b) for supplying the cooling air to the openings (4c, 6c).
Can be provided. In this case, the turbulent flow generation means (18) has a stagnation point (15
It is preferable that the cooling effect of the transition piece (4) at a position away from the upstream of () is greater than the cooling effect of the transition piece (4) at a position upstream of the stagnation point (15). More specifically, as the turbulent flow generation means (18), a plurality of pin fins (18) provided so as to cross the cooling air passages (4b, 6b) can be used. In this case, the pin fin (18
) Is a pin fin (1) at a position away from the upstream of the stagnation point (15) of the leading edge of the stationary blade (5).
Preferably, the density of 8) is higher than the density of the pin fins (18) at a position upstream of the stagnation point (15).

As described above, the structure of the joint portion between the transition piece (4) and the stationary blade shroud (6) has the structure of the transition piece seal (11) provided in the gap between the transition piece (4) and the stationary blade shroud (6). However, it is particularly suitable for a gas turbine having a structure that is supported so as to be separated from the flow path of the combustion gas (3a).

According to the present invention, it is possible to effectively prevent burning of the gap portion between the combustor tail cylinder and the stationary blade shroud due to the nonuniformity of the pressure of the combustion gas in the circumferential direction of the stationary blade row. Can do.

(First embodiment)
As shown in FIG. 5, a gas turbine 10 according to an embodiment of the present invention includes compressed air 1
a compressor 1 for generating a (only part of which is shown), and a casing 2 to which the generated compressed air 1a is supplied
And. A combustor 3 that generates combustion gas 3 a is provided inside the passenger compartment 2. A tail cylinder 4 is provided at the rear end of the combustor 3. The turbine of the gas turbine 10 is provided on the downstream side of the tail cylinder 4. More specifically, a first-stage stationary blade 5 and a stationary blade shroud 6 that supports the stationary blade 5 are provided on the downstream side of the tail cylinder 4. A moving blade 7 is provided downstream of the stationary blade 5. The combustion gas 3 a is introduced into the stationary blade 5 through the tail cylinder 4, the direction is changed by the stationary blade 5, and the fuel gas 3 a is injected into the moving blade 7.

FIG. 6 is an enlarged view of a joint portion between the transition piece 4 of the combustor 3 and the stationary blade shroud 6. Combustor 3
A flange 8 is joined to the tail cylinder 4 on the side opposite to the gas flow path through which the combustion gas 3a flows. Similarly, the stationary blade shroud 6 is provided with a flange 9 on the side opposite to the gas flow path through which the combustion gas 3a flows. A transition piece seal 11 is interposed between the flanges 8 and 9.
As a result, the tail cylinder 4 and the stationary blade shroud 6 are connected.

The tail tube 4 has a rear end 4a so that the tail tube seal 11 is not directly exposed to the combustion gas 3a.
However, it has a structure that extends downstream from the flange 8. The rear end portion 4a prevents the combustion gas 3a from being directly exposed to the tail tube seal 11.

As described above, in such a structure, the gap between the tail cylinder 4 and the stationary blade shroud 6, particularly the tail cylinder 4 and the stationary blade shroud 6, is caused by the non-uniformity of the pressure of the combustion gas 3 a. The problem is that the combustion gas 3a can enter the cavity 12 formed between them;
2 is a space surrounded by the tail cylinder 4, the stationary blade shroud 6 and the tail cylinder seal 11.

In this embodiment, in order to prevent the combustion gas 3a from entering the gap between the tail cylinder 4 and the stationary blade shroud 6, the cooling air 13 is introduced into the rear end portion 4a of the tail cylinder 4 at the stationary blade shroud. 6 is provided with an opening 4c for spraying toward the front end 6a. In order to inject the cooling air 13, the cooling air passage 4 b is formed so as to communicate with the opening 4 c positioned facing the front end portion 6 a of the stationary blade shroud 6. The cooling air 13 ejected from the opening 4c functions as sealing air, and therefore, the combustion gas 3a is prevented from entering the gap between the tail cylinder 4 and the stationary blade shroud 6.

Since supplying the cooling air to the rear end 4a of the tail cylinder 4 is originally necessary for cooling the rear end 4a, even if the cooling air 13 is jetted toward the stationary blade shroud 6, In addition, the compressed air 1a is not consumed. This is preferable in order not to deteriorate the performance of the gas turbine 10 due to an increase in the consumption of the compressed air 1a.

(Second embodiment)
The ejection of the cooling air may be performed from the front end portion 6 a of the stationary blade shroud 6. Second implementation
In the embodiment, as shown in FIG. 7, a cooling air passage 6 b communicating with the opening 6 c is provided in the front end portion 6 a of the stationary blade shroud 6, and cooling is performed from the opening 6 c toward the rear end portion 4 a of the tail cylinder 4. Air 14 is ejected. The jetted cooling air 14 functions as sealing air, and therefore, the intrusion of the combustion gas 3a into the gap between the tail cylinder 4 and the stationary blade shroud 6 is prevented.

(Third embodiment)
The ejection of the cooling air may be performed from both the tail cylinder 4 and the stationary blade shroud 6. In the third embodiment, as shown in FIG. 8, it is also preferable that openings are provided in both the rear end portion 4a of the transition piece 4 and the front end portion 6a of the stationary blade shroud 6; Then, the opening provided in the rear end part 4a of the tail cylinder 4 is referred to by reference numeral 4c, and the opening provided in the front end part 6a of the stationary blade shroud 6 is referred to by reference numeral 6c. In this case, the openings 4c and the openings 6c are preferably arranged alternately.

(Fourth embodiment)
It is important to prevent the combustion gas 3a from entering the gap between the tail cylinder 4 and the stationary blade shroud 6 with a smaller amount of cooling air to reduce the consumption of the compressed air 1a. For this purpose, the amount of cooling air jetted in the circumferential direction may be made non-uniform in accordance with the pressure distribution of the combustion gas 3a. More specifically, a relatively large amount of cooling air is ejected at a position in the gap where the combustion gas 3a is likely to enter, that is, upstream of the stagnation point of the leading edge of the stationary blade 5, and is separated from the stagnation point. A relatively small amount of cooling air may be ejected to the portion.

In the fourth embodiment, a technique for effectively using cooling air is provided by making the amount of cooling air jetted non-uniform in the week direction in accordance with the pressure distribution of the combustion gas 3a.

Referring to FIG. 9, in the fourth embodiment, the distribution of the cooling air ejection amount is controlled by the density of the openings 4c of the tail cylinder 4; the density of the openings 4c is the opening 4c per unit area. The number of More specifically, in the fourth embodiment, the density of the opening 4 c that ejects the cooling air 13 from the rear end 4 a of the tail cylinder 4 is high at a position upstream of the stagnation point 15 at the front edge of the stationary blade 5. , Low at a position away from the stagnation point 15. Such an arrangement of the opening 4c is such that a relatively large amount of cooling air is ejected to a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and the combustion gas is directed in the direction of entering the gap in the vicinity of the stagnation point 15. It is possible to effectively block the flow of 3a with less cooling air.

Similarly, the configuration in which the cooling air 14 is ejected from the front end portion 6a of the stationary blade shroud 6 (FIG. 7) and the configuration in which the cooling air is ejected from both the tail cylinder 4 and the stationary blade shroud 6 (FIG. 8) The distribution of the ejection amount of the cooling air can be controlled by the density. Front end 6a of stationary blade shroud 6
When the cooling air 14 is ejected from the front end 6a of the stationary blade shroud 6, the density of the opening 6c that ejects the cooling air 14 is high upstream of the stagnation point 15 at the front edge of the stationary blade 5, and the stagnation point 15
It is preferable that the distance is low at a position away from. When cooling air is ejected from both the tail cylinder 4 and the stationary blade shroud 6, the opening 4c of the tail cylinder 4 and the opening 6c of the stationary blade shroud 6 are used.
The density of is preferably high at the upstream of the stagnation point 15 at the leading edge of the stationary blade 5 and low at a position relatively away from the stagnation point 15.

(Fifth embodiment)
The amount of cooling air ejected can also be controlled by the size of the opening through which the cooling air is ejected. The same effect can be obtained by increasing the opening for ejecting the cooling air at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and decreasing it at a position relatively distant from the stagnation point 15.

Specifically, in the fifth embodiment, as shown in FIG. 10, the width of the opening 4 c of the tail cylinder 4 in the circumferential direction (direction in which the stationary blades 5 are arranged) is equal to that of the leading edge of the stationary blade 5. Wide at a position upstream of the stagnation point 15 and narrow at a position relatively far from the stagnation point 15. By determining the size of the opening 4c in this way, a relatively large amount of cooling air is ejected to a portion near the stagnation point of the leading edge of the stationary blade 5 and enters the gap in the vicinity of the stagnation point 15. The flow of the combustion gas 3a can be effectively interrupted with less cooling air.

The same technique is also used in the configuration in which the cooling air 14 is ejected from the front end portion 6a of the stationary blade shroud 6 (FIG. 7) and the configuration in which the cooling air is ejected from both the tail cylinder 4 and the stationary blade shroud 6 (FIG. 8). It can be adopted.

(Sixth embodiment)
Also in the sixth embodiment, similarly to the fifth embodiment, the ejection amount of the cooling air is controlled by the size of the opening that ejects the cooling air. However, in the sixth embodiment, as shown in FIG. 11, the amount of cooling air ejected is in the radial direction (the direction perpendicular to both the direction in which the stationary blades 5 are arranged and the direction in which the combustion gas 3a flows). It is controlled by the width of the opening 4c of the tail cylinder 4. In the present embodiment, the width of the opening 4 c of the tail pipe 4 in the radial direction is large at a position upstream of the stagnation point 15 on the front edge of the stationary blade 5 and is small at a position relatively away from the stagnation point 15. By determining the size of the opening 4c in this way, a relatively large amount of cooling air is ejected to a portion near the stagnation point of the leading edge of the stationary blade 5 and enters the gap in the vicinity of the stagnation point 15. The flow of the combustion gas 3a can be effectively interrupted with less cooling air.

Similarly, the configuration in which the cooling air 14 is ejected from the front end portion 6a of the stationary blade shroud 6 (FIG. 7) and the configuration in which the cooling air is ejected from both the tail cylinder 4 and the stationary blade shroud 6 (FIG. 8) The distribution of the ejection amount of the cooling air can be controlled by the size. The size of the opening can be adjusted by the width in the circumferential direction, and can also be adjusted by the width in the radial direction.

(Seventh embodiment)
In order to prevent the combustion gas 3a from entering the gap between the tail cylinder 4 and the stationary blade shroud 6, the cooling air flows from the rear end portion 4a of the tail cylinder 4 to the front end portion 6a of the stationary blade shroud 6 (or the stationary blade). It is important that the front end 6a of the shroud 6 reaches the rear end 4a of the transition piece 4 reliably. In the seventh embodiment, a structure for preventing the intrusion of the combustion gas 3a is provided by increasing the penetration force of the cooling air.

More specifically, in the seventh embodiment, as shown in FIG. 12, the shape of the cooling air passage 4b of the tail cylinder 4 is narrowed in the vicinity of the opening 4c, and the speed of the cooling air 13 to be ejected is Has been enhanced. In other words, the cooling air passage 4b is tapered toward the downstream side. Such a shape of the cooling air passage 4b increases the penetration force of the cooling air 13 from the tail cylinder 4 to the stationary blade shroud 6, and more effectively prevents the combustion gas 3a from entering the gap.

A similar technique can be applied to the stationary blade shroud 6. That the cooling air passage 6b of the stationary blade shroud 6 is throttled in the vicinity of the opening 6c (that is, the cooling air passage 6b is formed to taper upstream) prevents the combustion gas 3a from entering the gap. It is effective for.

(Eighth embodiment)
As explained in the background art, in the gap between the transition piece 4 and the stationary blade shroud 6, the combustion gas 3 a enters the gap in the vicinity of the stagnation point 15 on the leading edge of the stationary blade 5, and two adjacent stagnations occur. A flow in which compressed air flows out of the gap is likely to occur at a position in the middle of the point 15.
In the eighth embodiment, a structure for suppressing the occurrence of such a flow is provided.

FIGS. 13A to 13D are conceptual diagrams showing the structure of the joint between the tail cylinder 4 and the stationary blade shroud 6 in the eighth embodiment; FIG. 13A is the tail cylinder 4, the stationary blade 5 and the stationary blade shroud. 6 is a cross-sectional view taken along the line AA ′ of FIG. 13A, and FIG. 13C is a cross-sectional view taken along the line BB ′ of FIG. 13A. FIG. 13D is a view of the stationary blade 5 and the stationary blade shroud 6 as viewed from the upstream side. 13A to 13D, among the cooling air passages 4b, the cooling air passages (cross section AA ′) located upstream of the stagnation point 15 at the leading edge of the stationary blade 5.
Is referred to by reference numeral 4b-1, and a cooling air passage at a middle position between two adjacent stagnation points 15 is referred to by reference numeral 4b-2. In FIG. 13B, the opening of the cooling air passage 4b-1 is referred to by reference numeral 4c-1, and the cooling air ejected from the opening 4c-1 is referred to by reference numeral 13-1. In addition, in FIG. 13C, the opening of the cooling air passage 4b-2 is referred to by reference numeral 4c-2, and the cooling air ejected from the opening 4c-2 is referred to by reference numeral 13-2.

In the present embodiment, as shown in FIG. 13B, the tip of the cooling air passage 4b-1 located upstream of the stagnation point 15 at the leading edge of the stationary blade 5 is burned in the vicinity of the opening 4c-1. Gas 3a
It is tilted to the side that flows. As a result, the cooling air 1 is located upstream of the stagnation point 15 at the leading edge of the stationary blade 5.
3-1 is ejected toward the flow path side of the combustion gas 3a.

On the other hand, as shown in FIG. 13C, the tip of the cooling air passage 4b-2 located away from the stagnation point 15 on the leading edge of the stationary blade 5 is in the vicinity of the opening 4c-1, so that the combustion gas 3a is not present. Tilt to the opposite side of the flow side. As a result, the cooling air 13-2 is ejected toward the opposite side of the flow path of the combustion gas 3a at a position away from the stagnation point 15 at the leading edge of the stationary blade 5.

Since the cooling air passage 4b is formed in such a shape, as shown in FIG. 13D, the combustion gas 3a enters the gap in the vicinity of the stagnation point 15 on the leading edge of the stationary blade 5, and stagnation occurs. A flow in which compressed air flows out of the gap at a position in the middle of the point 15 is canceled. This is effective for preventing the combustion gas 3a from entering the gap.

The same technique can be applied to the cooling air passage 6b of the stationary blade shroud 6. in this case,
The front end of the cooling air passage 6b for injecting the cooling air 14 to a position upstream of the stagnation point 15 at the leading edge of the stationary blade 5 is inclined toward the side where the combustion gas 3a flows in the vicinity of the opening 6c. The front end of the cooling air passage 6b that ejects the cooling air 14 to the middle position of the stagnation point 15 on the front edge is inclined toward the opposite side of the flow path of the combustion gas 3a in the vicinity of the opening 6c. Such a structure of the cooling air passage 6b is effective for preventing the combustion gas 3a from entering the gap.

(Ninth embodiment)
14A and 14B are conceptual diagrams showing the structure of the joint portion between the tail cylinder 4 and the stationary blade shroud 6 in the ninth embodiment of the present invention; FIG. 14A shows the tail cylinder 4 and the stationary blade shroud 6; FIG. 14B is a view of the tail cylinder 4 seen from the downstream side.

In the ninth embodiment, as shown in FIG. 14A, the opening 4c for ejecting the cooling air 13 from the tail cylinder 4 is formed in a slit shape so as to extend in the circumferential direction. Accordingly, the cooling air passage 4b is also formed in a slit shape so as to extend in the circumferential direction. Such a shape of the opening 4c makes it possible to eject the cooling air 13 in a film shape and more uniformly suppress the intrusion of the combustion gas 3a into the gap.

A similar technique can be applied to the stationary blade shroud 6. In this case, the opening 6c for ejecting the cooling air 14 from the stationary blade shroud 6 is formed in a slit shape so as to extend in the circumferential direction. Such a shape of the opening 6c makes it possible to eject the cooling air 14 in a film shape and more uniformly suppress the intrusion of the combustion gas 3a into the gap.

(Tenth embodiment)
As described in the seventh embodiment, the shape of the cooling air passage 4b is preferably restricted in the vicinity of the opening 4c. In the tenth embodiment, as shown in FIGS. 15A and 15B, the opening 4c is formed in a slit shape, and the shape of the cooling air passage 4b is narrowed in the vicinity of the opening 4c. Such a shape of the cooling air passage 4b is suitable for uniformly suppressing the intrusion of the combustion gas 3a into the gap while increasing the penetration force of the cooling air 13.

A similar technique can be applied to the stationary blade shroud 6. In this case, the opening 6c for ejecting the cooling air 14 from the stationary blade shroud 6 is formed in a slit shape so as to extend in the circumferential direction. In addition, the shape of the cooling air passage 6b is narrowed in the vicinity of the opening 6c. Such a shape of the cooling air passage 4b is suitable for uniformly suppressing the penetration of the combustion gas 3a into the gap while increasing the penetration force of the cooling air 14.

(Eleventh embodiment)
As described in the fourth to sixth embodiments, a portion where a relatively large amount of cooling air is ejected to a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and away from the stagnation point 15 It is effective to eject a relatively small amount of cooling air in order to suppress the intrusion of the combustion gas 3a into the gap with a small amount of cooling air.

In the eleventh embodiment, a structure for realizing such distribution of cooling air in a structure in which openings are formed in a slit shape is provided. As shown in FIG.
In one embodiment, the width of the opening 4 c in the radial direction is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and narrowed at a portion away from the stagnation point 15. Thereby, a preferable distribution of the cooling air is realized, and the penetration of the combustion gas 3a into the gap can be effectively suppressed.

A similar technique can be applied to the stationary blade shroud 6. In this case, the opening 6c for ejecting the cooling air 14 from the stationary blade shroud 6 is formed in a slit shape so as to extend in the circumferential direction. The width of the opening 6 c in the radial direction is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and is narrowed at a portion away from the stagnation point 15. Thereby, a preferable distribution of the cooling air is realized, and the penetration of the combustion gas 3a into the gap can be effectively suppressed.

(Twelfth embodiment)
As described in the eighth embodiment, in order to suppress the intrusion of the combustion gas 3a, the combustion gas 3a enters the gap in the vicinity of the stagnation point 15 at the leading edge of the stationary blade 5, and the stagnation point 15 It is effective to cancel the flow in which compressed air flows out of the gap at an intermediate position. For this purpose, the cooling air 13 is injected at an upstream side of the stagnation point 15 at the leading edge of the stationary blade 5 while being inclined toward the flow path of the combustion gas 3a, and at an intermediate position between the adjacent stagnation points 15, It is effective to inject the cooling air 13 while inclining it toward the side opposite to the flow path of the combustion gas 3a.

In the twelfth embodiment, there is provided a structure for realizing injection of the cooling air 13 in a suitable direction in a structure in which an opening is formed in a slit shape. 17A to 17C are conceptual diagrams showing the structure of the rear end portion 4a of the transition piece 4 in the twelfth embodiment; in detail, FIG.
FIG. 17B is a view of the tail tube 4 viewed from the downstream side, and FIG. 17B is a cross-sectional view of the rear end portion 4a of the tail tube 4 in the CC ′ cross section (the cross section located upstream of the stagnation point 15). 17C is a cross-sectional view of the rear end portion 4a of the tail cylinder 4 in a DD ′ cross section (a cross section located in the middle of two adjacent stagnation points 15).

In the twelfth embodiment, as shown in FIG. 17A, the opening 4c of the tail cylinder 4 is formed in a wave shape, whereby the cooling air 13 is injected in a suitable direction. Specifically, as shown in FIG. 17B, in the CC ′ section located upstream of the stagnation point 15, the tip of the cooling air passage 4b is located on the side where the combustion gas 3a flows in the vicinity of the opening 4c. Tilted. Thereby, the cooling air 13 is jetted toward the flow path side of the combustion gas 3a upstream of the stagnation point 15 at the leading edge of the stationary blade 5.

On the other hand, as shown in FIG. 17C, D located in the middle of the stagnation point 15 on the leading edge of the stationary blade 5.
In the −D ′ cross section, the tip of the cooling air passage 4b is inclined to the side opposite to the side through which the combustion gas 3a flows in the vicinity of the opening 4c. Thereby, at a position away from the stagnation point 15 on the leading edge of the stationary blade 5, the cooling air 13 is ejected toward the opposite side of the flow path of the combustion gas 3a.

Since the cooling air passage 4b is formed in such a shape, the combustion gas 3a enters the gap in the vicinity of the stagnation point 15 at the leading edge of the stationary blade 5, and the compressed air flows at a position intermediate the stagnation point 15. The flow that flows out of the gap is canceled. This is effective for preventing the combustion gas 3a from entering the gap.

The same technique can be applied to the cooling air passage 6b of the stationary blade shroud 6. in this case,
At a position upstream of the stagnation point 15, the tip of the cooling air passage 6b is inclined toward the side where the combustion gas 3a flows in the vicinity of the opening 6c. Further, at the middle position of the stagnation point 15 at the front edge of the stationary blade 5, the tip of the cooling air passage 6b is inclined to the side opposite to the side through which the combustion gas 3a flows in the vicinity of the opening 6c. Such a structure of the cooling air passage 6b is effective for preventing the combustion gas 3a from entering the gap.

(Thirteenth embodiment)
The techniques described in the tenth to twelfth embodiments can be implemented in combination. In the thirteenth embodiment, a structure for realizing a combination of the techniques of the tenth to twelfth embodiments is provided.

18A to 18C are conceptual diagrams showing the structure of the rear end portion 4a of the transition piece 4 in the thirteenth embodiment; in detail, FIG. 18A is a view of the transition piece 4 as viewed from the downstream side; FIG. 18B shows C
FIG. 18C is a cross-sectional view of the rear end portion 4a of the tail cylinder 4 in a cross section −C ′ (a cross section located upstream of the stagnation point 15), and FIG. 18C illustrates a cross section DD ′ (in the middle of two adjacent stagnation points 15). It is sectional drawing of the rear-end part 4a of the tail cylinder 4 in the cross section located.

In the thirteenth embodiment, as shown in FIGS. 18B and 18C, the opening 4c is formed in a slit shape, and the shape of the cooling air passage 4b is narrowed in the vicinity of the opening 4c.

Further, as shown in FIG. 18A, the width of the opening 4 c in the radial direction is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and narrowed at a portion away from the stagnation point 15. .

In addition, as shown in FIG. 18B, in the CC ′ section located upstream of the stagnation point 15, the tip of the cooling air passage 4b is inclined toward the side where the combustion gas 3a flows in the vicinity of the opening 4c. It is done. Thereby, the cooling air 13 is jetted toward the flow path side of the combustion gas 3a upstream of the stagnation point 15 at the leading edge of the stationary blade 5.

On the other hand, as shown in FIG. 18C, D located in the middle of the stagnation point 15 on the leading edge of the stationary blade 5
In the −D ′ cross section, the tip of the cooling air passage 4b is inclined to the side opposite to the side through which the combustion gas 3a flows in the vicinity of the opening 4c. Thereby, at a position away from the stagnation point 15 on the leading edge of the stationary blade 5, the cooling air 13 is ejected toward the opposite side of the flow path of the combustion gas 3a.

The formation of the cooling air passage 4b in such a shape is effective for preventing the combustion gas 3a from entering the gap. It is obvious to those skilled in the art that the same technique can be applied to the stationary blade shroud 6.

(Embodiment 14)
As already described in the fourth to sixth embodiments, a relatively large amount of cooling air is ejected to a position upstream of the stagnation point 15, and a relatively small amount of cooling air is disposed at an intermediate position of the stagnation point 15. Is effective to suppress the intrusion of the combustion gas 3a into the gap between the tail cylinder 4 and the stationary blade shroud 6 with a small amount of cooling air.

However, if the amount of cooling air is not uniform, the flow rate of the cooling air flowing through the cooling air passage 4b of the tail cylinder 4 (or the cooling air passage 6b of the stationary blade shroud 6) becomes non-uniform. The temperature of 4 (or the stationary blade shroud 6) becomes uneven. More specifically, itching point 15
The temperature of the transition piece 4 at a position upstream is lower, and the temperature of the transition piece 4 at a middle position of the stagnation point 15 is increased. This is not preferable because thermal stress is generated in the tail cylinder 4 (or the stationary blade shroud 6).

In order to eliminate the non-uniformity of the temperature of the transition piece 4 due to the non-uniformity of the cooling air ejection amount,
It is effective to increase the cooling effect of the transition piece 4 at the intermediate position of the stagnation point 15 relative to the cooling effect of the transition piece 4 at the position upstream of the stagnation point 15. In the fourteenth embodiment, the cooling effect of the transition piece 4 at the intermediate position of the stagnation point 15 is the same as that of the transition piece 4 at the upstream position of the stagnation point 15.
There is provided a technique for relatively improving the cooling effect.

19A and 19B are conceptual diagrams specifically showing the structure of the joint portion of the transition piece 4 and the stationary blade shroud 6 in the fourteenth embodiment; FIG. 19A shows the joint portion of the flow path of the combustion gas 3a. FIG. 19B is a cross-sectional view showing the structure of a cooling air passage (referred to by reference numeral 4b-3) for injecting the cooling air 13 to an intermediate position of the stagnation point 15.

In the present embodiment, the density of the openings 4 c for ejecting the cooling air 13 from the rear end portion 4 a of the tail cylinder 4 is high at a position upstream of the stagnation point 15 on the front edge of the stationary blade 5, and is intermediate between the stagnation points 15. Low in position. As described above, such an arrangement of the opening 4c suppresses the intrusion of the combustion gas 3a, but causes nonuniformity of the temperature of the tail cylinder 4.

In order to eliminate the non-uniformity of the temperature of the transition piece 4, in the present embodiment, the cooling air passage 4 b-3 located in the middle of the stagnation point 15 is provided with a protrusion 16 that functions as a turbulent flow generation means. The protrusion 16 generates a turbulent flow in the cooling air inside the cooling air passage 4b-3, and improves the cooling effect of the tail cylinder 4 by the cooling air. By providing the protrusion 16, the temperature of the transition piece 4 at the middle position of the stagnation point 15 is lowered, and the uniformity of the temperature of the transition piece 4 is improved.

As shown in FIG. 19C, a cooling air passage (referred to by reference numeral 4b-4) for ejecting the cooling air 13 upstream of the stagnation point 15 is also provided with a projection 17 that functions as a turbulent flow generation means. It is also possible. Providing the protrusion 17 in the cooling air passage 4b-4 is effective for cooling the tail cylinder 4 with a small amount of cooling air.

If the protrusion 17 is provided in the cooling air passage 4b-4, the height h ₂ of the protrusions 17, than the height h ₁ of the protrusions 16 provided in the cooling air passage 4b-3 located in the middle of the stagnation point 15 Lowered. Such a configuration makes the cooling effect of the transition piece 4 at a position intermediate the stagnation point 15 relatively higher than the cooling effect of the transition piece 4 at a position upstream of the stagnation point 15, and makes the temperature of the transition piece 4 uniform. It is effective for.

However, it should be noted that the present invention is not limited to the configuration in which the protrusion 17 is provided in the cooling air passage 4b-4. In the configuration in which the protrusion 17 is not provided in the cooling air passage 4b-4,
This is effective for making the cooling effect of the transition piece 4 at the intermediate position of the stagnation point 15 higher than the cooling effect of the transition piece 4 at the position upstream of the stagnation point 15 and making the temperature of the transition piece 4 uniform.

The same technique can also be applied to a configuration (fifth and sixth embodiments) in which the amount of cooling air ejected is controlled by the size of the opening 4c of the tail cylinder 4. Also in this case, a relatively high protrusion is provided in the cooling air passage 4b for ejecting the cooling air at a position intermediate the stagnation point 15, and the cooling air passage for ejecting the cooling air to a position upstream of the stagnation point 15. 4b is provided with a relatively low protrusion. It is possible that no projection is provided in the cooling air passage 4b that ejects the cooling air to a position upstream of the stagnation point 15.

In addition, the same technique can be applied to the cooling air passage 6 b of the stationary blade shroud 6. In this case, a relatively high protrusion is provided in the cooling air passage 6b for ejecting the cooling air at a position intermediate the stagnation point 15, and the cooling air passage 6b for ejecting the cooling air to a position upstream of the stagnation point 15 is provided. Are provided with relatively low protrusions. It is possible that no projection is provided in the cooling air passage 6b for discharging the cooling air to a position upstream of the stagnation point 15.

(Embodiment 15)
As described in the fourteenth embodiment, in order to eliminate the non-uniformity of the temperature of the tail tube 4, the cooling effect of the tail tube 4 at the intermediate position of the stagnation point 15 is set upstream of the stagnation point 15. It is effective to make it relatively higher than the cooling effect of the transition piece 4 at the position. In the fifteenth embodiment,
The tail cylinder 4 at the intermediate position of the stagnation point 15 by an approach different from that of the fourteenth embodiment.
This cooling effect is relatively higher than the cooling effect of the transition piece 4 at the position upstream of the stagnation point 15.

More specifically, in the fifteenth embodiment, as shown in FIGS. 20A and 20B,
The density of the protrusions 16 provided in the cooling air passage 4b-3 located in the middle of the stagnation point 15 is made higher than the density of the protrusions 17 provided in the cooling air passage 4b-4 located upstream of the stagnation point 15; The density of is the number of protrusions provided per unit area of the inner surface of the cooling air passage. By determining the density of the protrusions in this way, the cooling effect of the transition piece 4 at the intermediate position of the stagnation point 15 is relatively higher than the cooling effect of the transition piece 4 at the position upstream of the stagnation point 15. The temperature of 4 is made more uniform.

The same technique can also be applied to a configuration (fifth and sixth embodiments) in which the amount of cooling air ejected is controlled by the size of the opening 4c of the tail cylinder 4. Also in this case, the density of the protrusions provided in the cooling air passage 4b that ejects the cooling air to the middle position of the stagnation point 15 is provided in the cooling air passage 4b that ejects the cooling air to a position upstream of the stagnation point 15. It is relatively higher than the density of the protrusions.

In addition, the same technique can be applied to the cooling air passage 6 b of the stationary blade shroud 6. In this case, the density of the projections provided in the cooling air passage 6b that ejects cooling air to the middle position of the stagnation point 15 is equal to the density of the projections provided in the cooling air passage 6b that ejects cooling air to the position upstream of the stagnation point 15. It is relatively higher than the density. Thereby, the temperature of the stationary blade shroud 6 is made more uniform.

(Sixteenth embodiment)
As described in the eleventh embodiment, the amount of cooling air jetted out is not uniform.
This is also effective in a structure in which the opening 4c of the tail cylinder 4 is formed in a slit shape. In the eleventh embodiment, the width of the opening 4 c in the radial direction is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and narrowed at a portion away from the stagnation point 15.

However, as explained in the fourteenth and fifteenth embodiments, the cooling air ejection amount is made non-uniform, and the temperature of the tail cylinder 4 is made non-uniform. In the sixteenth embodiment, when the structure in which the opening 4c of the transition piece 4 is formed in a slit shape is adopted, the temperature non-uniformity of the transition piece 4 caused by the distribution of the cooling air ejection amount is eliminated. A structure for providing is provided.

21A to 21C are schematic views showing the structure of the joint portion between the transition piece 4 and the stationary blade shroud 6 in the sixteenth embodiment; FIG. 21A shows the joint portion from the flow path side of the combustion gas 3a. FIG. 21B is a view of the rear end portion 4a of the transition piece 4 viewed from the downstream side, and FIG. 21C is a structure of the rear end portion 4a of the transition piece 4 in the section EE ′ of FIG. 21B. FIG.

In the present embodiment, as shown in FIG. 21B, the width of the opening 4c in the radial direction is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and is away from the stagnation point 15. Narrowed. As described above, the shape of the opening 4c suppresses the intrusion of the combustion gas 3a, but causes a non-uniform temperature of the tail tube 4.

In order to eliminate the nonuniformity of the temperature of the transition piece 4, in the present embodiment, the cooling air passage 4b
Pin fins 18 are provided so as to traverse it. The pin fin 18 functions as turbulent flow generation means for generating turbulent flow in the cooling air. The density of the pin fins 18 is made non-uniform. More specifically, the density of the pin fins 18 is relatively high at a position intermediate the stagnation point 15 and relatively low at a position upstream of the stagnation point 15. Such an arrangement of the pin fins 18 gives the cooling effect of the transition piece 4 at the intermediate position of the stagnation point 15 to the stagnation point 15.
This is relatively higher than the cooling effect of the transition piece 4 at the upstream position, and is effective in making the temperature of the transition piece 4 uniform.

The same technique can be applied to the cooling air passage 6b of the stationary blade shroud 6. in this case,
Pin fins functioning as turbulent flow generation means are provided in the cooling air passage 6b, and the density of the pin fins is relatively high at a position intermediate the stagnation point 15 and relatively low at a position upstream of the stagnation point 15. Such an arrangement of pin fins is effective in making the temperature of the stationary blade shroud 6 uniform.

(Embodiment 17)
As described in the fourteenth to sixteenth embodiments, the non-uniformity of the cooling air ejection amount causes the non-uniformity of the temperature of the tail cylinder 4 and causes the generation of thermal stress. In the seventeenth embodiment, the temperature uniformity of the transition piece 4 is improved by an approach different from the fourteenth to sixteenth embodiments.

22A and 22B are conceptual diagrams showing the structure of the joint portion between the transition piece 4 and the stationary blade shroud 6 in the seventeenth embodiment; FIG. 22A shows the joint portion from the flow path side of the combustion gas 3a. FIG. 22B is a view of the rear end portion 4a of the transition piece 4 as seen from the downstream side. In the present embodiment, the two stationary blades 5 are positioned downstream of the vertical wall surface 4 d (surface parallel to the radial direction) of the tail cylinder 4, and the other stationary blade 5 is the center of the tail cylinder 4. Located downstream of the section. In the present embodiment, the combustor 3 generates the combustion gas 3a in such a form that the central part of the transition piece 4 is hotter than the peripheral part. The stationary blades positioned downstream of the vertical wall surface of the transition piece 4 are hereinafter referred to as stationary blades 5-1 and 5-2, and the stationary blades positioned downstream of the center part of the transition piece 4 are hereinafter referred to as stationary blades 5. -3.

As shown in FIG. 22A, in the seventeenth embodiment, the density of the opening 4c that ejects the cooling air 13 from the rear end 4a of the tail cylinder 4 (that is, the density of the cooling air passage 4b) is the central portion. At a position upstream of the stagnation point 15 of the leading edge of the stationary blade 5-3 located at the
Low at a distance from Such an arrangement of the opening 4c causes a relatively large amount of cooling air to be ejected to a position upstream of the stagnation point 15 of the stationary blade 5-3 and enters a gap in the vicinity of the stagnation point 15 of the stationary blade 5-3. It is possible to effectively block the flow of the combustion gas 3a in the direction.

In addition, in the present embodiment, as shown in FIG. 22B, the high temperature portion of the tail tube 4 (that is, the central portion of the tail tube 4) is the stagnation point 15 of the leading edge of the stationary blade 5-3. Located upstream. As described above, since many cooling air passages 4b are provided upstream of the stagnation point 15 of the stationary blade 5-3, the rear end surface 4a of the tail cylinder 4 is located at a position facing the high temperature portion. A lot of cooling air is supplied,
The position facing the high temperature portion is effectively cooled. Thereby, the uniformity of the temperature of the transition piece 4 is improved.

A configuration in which a similar technique is used to control the amount of cooling air jetted by the size of the opening 4c of the tail cylinder 4 (
It is obvious to those skilled in the art that the present invention can also be applied to the fifth and sixth embodiments). Static blade 5
A relatively large opening 4 c is provided upstream of the stagnation point 15 at the front edge of the slag, and a large amount of cooling air is ejected upstream of the stagnation point 15. On the other hand, the hot portion of the tail cylinder 4 is the stagnation point 1 of the leading edge of the stationary blade 5.
The positions of the tail cylinder 4 and the stationary blade 5 are adjusted so as to be located upstream of the nozzle 5. As a result, the tail cylinder 4
The temperature uniformity is improved.

The same technique is also applicable when the opening 4c of the tail cylinder 4 is formed in a slit shape (see the eleventh embodiment). In this case, the width of the opening 4 c in the radial direction of the opening 4 c is wide at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and narrowed at a portion away from the stagnation point 15. As a result, a lot of cooling air is ejected upstream of the stagnation point 15. On the other hand, so that the hot part of the tail cylinder 4 is located upstream of the stagnation point 15 on the leading edge of the stationary blade 5,
The positions of the tail cylinder 4 and the stationary blade 5 are adjusted. Thereby, the uniformity of the temperature of the transition piece 4 is improved.

Furthermore, the same technique can be applied to a structure in which an opening for ejecting cooling air is provided in the stationary blade shroud 6. The density or size of the openings through which the cooling air is jetted is adjusted so that a large amount of cooling air is jetted upstream of the stagnation point 15 on the leading edge of the stationary blade 5, and the hot portion of the tail cylinder 4 is statically static. The positions of the tail cylinder 4 and the stationary blade 5 are adjusted so as to be located upstream of the stagnation point 15 at the leading edge of the blade 5. Thereby, the uniformity of the temperature of the stationary blade shroud 6 is improved.

(Eighteenth embodiment)
As described in the seventeenth embodiment, when a structure in which a large amount of cooling air is jetted upstream of the stagnation point 15 at the leading edge of the stationary blade 5 is employed, It is preferable to be located upstream of the stagnation point 15. In the eighteenth embodiment, a structure of the combustor 3 is provided for positioning the high temperature portion of the transition piece 4 upstream of the stagnation point 15.

More specifically, in the present embodiment, as shown in FIG.
The density of the openings 4 c for ejecting the cooling air 13 from a (that is, the density of the cooling air passage 4 b) is high at a position upstream of the stagnation point 15 on the leading edge of the stationary blade 5 and low at a position intermediate the stagnation point 15. . In addition, the fuel nozzle 19 of the combustor 3 is provided at a position corresponding to the upstream of the stagnation point 15 on the leading edge of the stationary blade 5.

Such a structure effectively improves the uniformity of the temperature of the transition piece 4. The temperature of the transition piece 4 is increased downstream of the fuel nozzle 19. Therefore, by providing the fuel nozzle 19 of the combustor 3 at a position corresponding to the upstream of the stagnation point 15 on the leading edge of the stationary blade 5, the high temperature portion of the tail cylinder 4 is positioned upstream of the stagnation point 15. In addition, as described above, since many cooling air passages 4b are provided upstream of the stagnation point 15 of the stationary blade 5, the cooling air passage 4b is located at a position facing the high temperature portion of the rear end portion 4a of the tail cylinder 4. A lot of cooling air is supplied. Thereby, the part facing the high temperature part of the tail tube 4 is
It is cooled effectively and the uniformity of the temperature of the transition piece 4 is improved.

A configuration in which a similar technique is used to control the amount of cooling air jetted by the size of the opening 4c of the tail cylinder 4 (
It is obvious to those skilled in the art that the present invention can also be applied to the fifth and sixth embodiments). In addition, it is obvious to those skilled in the art that the same technique can be applied to a structure in which an opening for ejecting cooling air is provided in the stationary blade shroud 6.

FIG. 1 is a cross-sectional view showing a structure of a joint portion between a transition piece and a stationary blade shroud in a conventional gas turbine. FIG. 2A is a cross-sectional view showing another structure of a joint portion between a transition piece and a stationary blade shroud in a conventional gas turbine. FIG. 2B is a cross-sectional view showing still another structure of the joint portion between the transition piece and the stationary blade shroud in the conventional gas turbine. FIG. 3 is a view of the structure of the joint portion between the transition piece and the stationary blade shroud in the conventional gas turbine as viewed from the side where the combustion gas flows. FIG. 4 is a perspective view showing how combustion gas enters the gap between the transition piece and the stationary blade shroud and compressed air flows out of the gap. FIG. 5 is a cross-sectional view showing the structure of a gas turbine according to the present invention. FIG. 6 is a cross-sectional view showing the structure of the joint between the tail cylinder and the stationary blade shroud in the gas turbine according to the first embodiment of the present invention. FIG. 7 is a cross-sectional view showing the structure of the joint between the transition piece and the stationary blade shroud in the second embodiment. FIG. 8 is a diagram showing the structure of the joint portion between the tail cylinder and the stationary blade shroud when viewed from the side through which the combustion gas flows in the third embodiment. FIG. 9 is a diagram showing the structure of the joint portion between the tail cylinder and the stationary blade shroud when viewed from the side through which the combustion gas flows in the fourth embodiment. FIG. 10 is a diagram showing the structure of the joint portion between the tail cylinder and the stationary blade shroud when viewed from the side through which the combustion gas flows in the fifth embodiment. FIG. 11 is a diagram illustrating the structure of the rear end portion of the transition piece when viewed from the downstream side in the sixth embodiment. FIG. 12 is a diagram showing the structure of the joint portion between the tail cylinder and the stationary blade shroud when viewed from the side through which the combustion gas flows in the seventh embodiment. FIG. 13A is a diagram illustrating a structure of a joint portion between a transition piece and a stationary blade shroud when viewed from the side through which combustion gas flows in the eighth embodiment. 13B is a cross-sectional view taken along the line A-A ′ of FIG. 13A. FIG. 13C is a cross-sectional view taken along the line B-B ′ of FIG. 13A. FIG. 13D is a view of the stationary blade and the stationary blade shroud as seen from the upstream side, and is a view for explaining the action of the structure of the eighth embodiment to suppress the invasion of combustion gas. FIG. 14A is a diagram showing a structure of a joint portion between a transition piece of a gas turbine and a stationary blade shroud when viewed from the side through which combustion gas flows in the ninth embodiment. FIG. 14B is a diagram illustrating the structure of the rear end portion of the transition piece as viewed from the downstream side in the ninth embodiment. FIG. 15A is a diagram illustrating a structure of a rear end portion of a transition piece of a gas turbine when viewed from the downstream side in the tenth embodiment. FIG. 15B is a cross-sectional view showing the structure of the rear end portion of the transition piece in the tenth embodiment. FIG. 16 is a diagram illustrating the structure of the rear end portion of the transition piece as viewed from the downstream side in the eleventh embodiment. FIG. 17A is a diagram illustrating the structure of the rear end portion of the transition piece as viewed from the downstream side in the twelfth embodiment. FIG. 17B is a cross-sectional view showing the structure of the rear end portion of the transition piece in the C-C ′ cross section (the cross section located upstream of the stagnation point 15) in FIG. 17A. FIG. 17C is a cross-sectional view showing the structure of the rear end portion of the transition piece in the D-D ′ cross section of FIG. 17A (a cross section positioned in the middle of two adjacent stagnation points 15). FIG. 18A is a diagram illustrating the structure of the rear end portion of the transition piece as viewed from the downstream side in the thirteenth embodiment. FIG. 18B is a cross-sectional view showing the structure of the rear end portion of the transition piece in the C-C ′ cross section (the cross section located upstream of the stagnation point 15) in FIG. 18A. 18C is a cross-sectional view showing the structure of the rear end portion of the transition piece in the D-D ′ cross section of FIG. 18A (a cross section positioned between two adjacent stagnation points 15). FIG. 19A is a diagram illustrating a structure of a joining portion of a transition piece and a stationary blade shroud when viewed from the combustion gas flow side in the fourteenth embodiment. FIG. 19B is a cross-sectional view showing a structure of a cooling air passage for injecting cooling air to an intermediate position between stagnation points in the fourteenth embodiment. FIG. 19C is a cross-sectional view showing a structure of a cooling air passage that ejects cooling air to a position upstream of the stagnation point in the fourteenth embodiment. FIG. 20A is a cross-sectional view showing a structure of a cooling air passage for injecting cooling air to an intermediate position between stagnation points in the fifteenth embodiment. FIG. 20B is a cross-sectional view showing a structure of a cooling air passage that ejects cooling air to a position upstream of the stagnation point in the fifteenth embodiment. FIG. 21A is a diagram illustrating a structure of a joining portion of a transition piece and a stationary blade shroud when viewed from the side through which combustion gas flows in the sixteenth embodiment. FIG. 21B is a diagram illustrating the structure of the rear end portion of the transition piece as viewed from the downstream side in the sixteenth embodiment. FIG. 21C is a diagram illustrating an arrangement of pin fins in the cooling air passage according to the sixteenth embodiment. FIG. 22A is a diagram illustrating a structure of a joining portion of a transition piece and a stationary blade shroud when viewed from the combustion gas flow side in the seventeenth embodiment. FIG. 22B is a diagram showing the structure of the rear end portion of the transition piece as viewed from the downstream side in the seventeenth embodiment. FIG. 23 is a conceptual diagram showing the structure of the combustor 3 in the eighteenth embodiment.

Explanation of symbols

1: Compressor 1a: Compressed air 2: Vehicle compartment 3: Combustor 3a: Combustion gas 4: Tail tube 4a: Rear end 4b: Cooling air passage 4c: Opening 5: Stator blade 6: Stator blade shroud 6a: Front end 6b: Cooling air passage 6c: Opening 7: Moving blade 8, 9: Flange 10: Gas turbine 11: Cylinder seal 12: Cavity 13, 14: Cooling air 15: Stagnation point 16, 17: Protrusion 18: Pin fin 19: Fuel Nozzle 101: transition piece 101a: flange 101b: rear end portion 102 stationary blade 103: stationary blade shroud 103a: flange 103b: front end portion 104: seal 104a: cooling air 105: combustion gas

Claims (24)

A combustor for injecting combustion gas from the tail cylinder;
A turbine to which the combustion gas is supplied from the transition piece,
The turbine is
With stationary vanes,
A stationary blade shroud that is located downstream of the transition piece and supports the stationary blade,
At least one opening for ejecting cooling air toward the upstream end of the stationary blade shroud is provided at the downstream end of the tail tube ,
The opening is configured such that the flow rate of the cooling air flowing into a position upstream of the stagnation point of the leading edge of the stationary blade in the gap is larger than the flow rate of the cooling air flowing into a position away from the stagnation point upstream of the gap. A gas turbine that is shaped to increase . A gas turbine according to claim 1, wherein
At least one opening for ejecting cooling air toward the downstream end of the tail cylinder is provided at the upstream end of the stationary blade shroud. A combustor including a transition piece;
A turbine,
The turbine is
With stationary vanes,
A stationary blade shroud that is located downstream of the transition piece and supports the stationary blade,
The upstream end of the stationary blade shroud is provided with at least one opening for ejecting cooling air toward the downstream end of the tail cylinder ,
The opening is configured such that the flow rate of the cooling air flowing into a position upstream of the stagnation point of the leading edge of the stationary blade in the gap is larger than the flow rate of the cooling air flowing into a position away from the stagnation point upstream of the gap. A gas turbine that is shaped to increase . A gas turbine according to any one of claims 1 to 3 ,
The combustor and the stationary blade are configured such that the temperature of the transition piece at a position upstream of the stagnation point is higher than that of other portions. The gas turbine according to claim 4 , wherein
The combustor includes a combustion nozzle at a position corresponding to the upstream of the stagnation point. A gas turbine according to any one of claims 1 to 3,
The cooling air passage for supplying the cooling air to the opening has a tapered shape toward the opening. A gas turbine according to claim 1, wherein
The at least one opening is
A first opening provided at a position upstream of the stagnation point of the leading edge of the stationary blade;
A second opening provided at an intermediate position of the stagnation point,
The transition piece is formed with a first cooling air passage for supplying the cooling air to the first opening and a second cooling air passage for supplying the cooling air to the second opening,
The downstream end of the first cooling air passage is inclined toward the surface of the tail cylinder through which the combustion gas flows,
A gas turbine in which an end on the downstream side of the second cooling air passage is inclined to a side opposite to the surface of the tail tube. A gas turbine according to claim 3, wherein
The at least one opening is
A first opening provided at a position upstream of the stagnation point of the leading edge of the stationary blade;
A second opening provided at an intermediate position of the stagnation point,
The stationary blade shroud is formed with a first cooling air passage for supplying the cooling air to the first opening and a second cooling air passage for supplying the cooling air to the second opening,
The downstream end of the first cooling air passage is inclined toward the surface of the stationary blade shroud through which the combustion gas flows,
The downstream end of the second cooling air passage is inclined to the side opposite to the surface of the stationary blade shroud. A gas turbine according to claim 1 or claim 3, wherein
The at least one opening is formed as a long slit in a direction in which the stationary blades are arranged. Gas turbine. A gas turbine according to claim 9 , wherein
The cooling air passage for supplying the cooling air to the opening has a tapered shape toward the opening. A gas turbine according to claim 9 , wherein
The width of the slit at a position upstream of the stagnation point of the leading edge of the stationary blade is wider than the width of the slit at a position away from the position upstream of the stagnation point. A gas turbine according to claim 11 , comprising:
The combustor and the stationary blade are configured such that the temperature of the transition piece at a position upstream of the stagnation point is higher than that of other portions. The gas turbine according to claim 12 ,
The combustor includes a combustion nozzle at a position corresponding to the upstream of the stagnation point. A gas turbine according to claim 1, wherein
The at least one opening is formed in a slit shape long in the direction in which the stationary blades are arranged,
The tail tube is formed with a slit-like cooling air passage for supplying the cooling air to the opening,
The cross section of the cooling air passage at a position upstream of the stagnation point of the leading edge of the stationary blade has a shape in which an end on the downstream side is inclined toward the surface of the tail tube where the combustion gas flows,
The cross section of the cooling air passage at a position away from the upstream of the stagnation point has a shape in which a downstream end is inclined to the side opposite to the surface of the tail tube. A gas turbine according to claim 3, wherein
The at least one opening is formed in a slit shape long in the direction in which the stationary blades are arranged,
The stationary blade shroud is formed with a slit-like cooling air passage for supplying the cooling air to the opening.
The cross section of the cooling air passage at a position upstream of the stagnation point of the leading edge of the stationary blade has a shape in which an end on the downstream side is inclined toward the surface of the stationary blade shroud through which the combustion gas flows. ,
The cross section of the cooling air passage at a position away from the upstream of the stagnation point has a shape in which an end on the downstream side is inclined to the side opposite to the surface of the stationary blade shroud. A gas turbine according to claim 1, wherein
The at least one opening is
A first opening provided at a position upstream of the stagnation point of the leading edge of the stationary blade;
A second opening provided at an intermediate position of the stagnation point,
The transition piece is formed with a first cooling air passage for supplying the cooling air to the first opening and a second cooling air passage for supplying the cooling air to the second opening,
In the second cooling air passage, turbulent flow generating means for causing turbulent flow in the cooling air is formed. Gas turbine. A gas turbine according to claim 3, wherein
The at least one opening is
A first opening provided at a position upstream of the stagnation point of the leading edge of the stationary blade;
A second opening provided at an intermediate position of the stagnation point,
The stationary blade shroud is formed with a first cooling air passage for supplying the cooling air to the first opening and a second cooling air passage for supplying the cooling air to the second opening,
In the second cooling air passage, turbulent flow generating means for causing turbulent flow in the cooling air is formed. Gas turbine. A gas turbine according to claim 16 or claim 17 , wherein
In the first cooling air passage, other turbulence generating means for causing turbulence in the cooling air is formed,
The turbulent flow generating means provided in the second cooling air passage is formed so that the cooling effect of the tail tube is higher than that of the other turbulent flow generating means provided in the first cooling air passage. gas turbine. A gas turbine according to claim 18 , comprising:
The turbulent flow generating means provided in the second cooling air passage includes a first protrusion protruding into the second cooling air passage;
The other turbulent flow generation means provided in the first cooling air passage includes a second protrusion protruding into the first cooling air passage,
The height of the first protrusion is higher than the height of the second protrusion. A gas turbine according to claim 18 , comprising:
The turbulent flow generating means provided in the second cooling air passage includes a first protrusion protruding into the second cooling air passage;
The other turbulent flow generation means provided in the first cooling air passage includes a second protrusion protruding into the first cooling air passage,
The density at which the first protrusions are provided is greater than the density at which the second protrusions are provided. A gas turbine according to claim 1, wherein
The at least one opening is formed in a slit shape long in the direction in which the stationary blades are arranged,
The tail tube is formed with a slit-like cooling air passage for supplying the cooling air to the opening,
The cooling air passage is provided with turbulent flow generating means for causing turbulent flow in the cooling air,
The turbulent flow generating means is configured such that the cooling effect of the tail tube at a position away from the upstream of the stagnation point of the leading edge of the stationary blade is greater than the cooling effect of the tail tube at a position upstream of the stagnation point. Formed in the gas turbine. A gas turbine according to claim 3, wherein
The at least one opening is formed in a slit shape long in the direction in which the stationary blades are arranged,
The stationary blade shroud is formed with a slit-like cooling air passage for supplying the cooling air to the opening.
The cooling air passage is provided with turbulent flow generating means for causing turbulent flow in the cooling air,
The turbulent flow generating means is configured such that the cooling effect of the tail tube at a position away from the upstream of the stagnation point of the leading edge of the stationary blade is greater than the cooling effect of the tail tube at a position upstream of the stagnation point. Formed in the gas turbine. A gas turbine according to claim 21 or claim 22 , wherein
The turbulent flow generation means includes a plurality of pin fins provided so as to cross the cooling air passage,
The pin fin is formed such that the density of the pin fin at a position away from the upstream of the stagnation point of the leading edge of the stationary blade is higher than the density of the pin fin at a position upstream of the stagnation point. A gas turbine according to any one of claims 1 to 23 , wherein
Furthermore, a tail cylinder seal provided in a gap between the tail cylinder and the stationary blade shroud is provided,
A gas turbine in which the tail cylinder and the stationary blade shroud are provided with a flange that supports the tail cylinder seal away from the combustion gas flow path.

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