JP6118596B2 - Elastic ring, combustor and gas turbine equipped with the same, and method for producing elastic ring - Google Patents

Description

The present invention is an elastic ring that is disposed between the outer peripheral side of the first cylinder and the inner peripheral side of the second cylinder and allows the displacement of the second cylinder relative to the first cylinder, a combustor and a gas turbine including the elastic ring, and The present invention relates to a method for manufacturing an elastic ring .

  The gas turbine includes a compressor that compresses air, a combustor that generates combustion gas by burning fuel in the air compressed by the compressor, and a turbine that is driven by the combustion gas from the combustor. Yes.

  A gas turbine combustor, for example, as described in Patent Document 1 below, a nozzle that injects fuel, an inner cylinder that covers the outer periphery of the nozzle, and fuel injected from the nozzle burns, And a tail tube that guides the combustion gas generated by the combustion to the turbine. The inner cylinder is arranged upstream in the main direction of the flow of combustion gas in the tail cylinder. The distal end portion of the inner cylinder is inserted on the inner peripheral side of the proximal end portion of the tail cylinder. Between the outer peripheral side of the distal end portion of the inner cylinder and the inner peripheral side of the proximal end portion of the tail cylinder, a cylindrical spring member that supports the tail cylinder to be displaceable with respect to the inner cylinder, and a distal end portion of the inner cylinder A cylindrical sealing member that seals between the outer peripheral side of the inner cylinder and the inner peripheral side of the proximal end portion of the tail cylinder is disposed.

Japanese Patent Laid-Open No. 2003-13747

  In the technique described in Patent Document 1, air from the compressor flows from the upstream side between the outer peripheral side of the distal end portion of the inner cylinder and the inner peripheral side of the proximal end portion of the tail cylinder. Part of this air passes through the cylindrical spring member and the cylindrical seal member disposed therebetween, and flows on the inner peripheral side of the tail cylinder and downstream of the spring member and the seal member. As described above, the air that flows on the inner peripheral side of the transition piece and downstream of the spring member and the seal member is used as cooling air for the inner peripheral surface of the transition piece or as air for fuel combustion. Is possible.

  However, when the air that flows on the inner peripheral side of the transition piece and downstream of the spring member or the seal member is used as cooling air or fuel combustion air on the inner peripheral surface of the transition piece, It is necessary to adjust the flow rate of this air appropriately.

Therefore, the present invention is arranged between the outer peripheral side of the first cylinder and the inner peripheral side of the second cylinder in which the distal end portion of the first cylinder is inserted on the inner peripheral side of the base end portion, It is an object of the present invention to provide an elastic ring capable of appropriately adjusting the flow rate of air flowing in from the side, a combustor and a gas turbine including the elastic ring, and a method for manufacturing the elastic ring .

The elastic ring of the combustor as one aspect according to the invention for achieving the above object is
A combustor comprising: a first cylinder; and a second cylinder in which a distal end, which is one side in the axial direction of the first cylinder, is inserted on the inner peripheral side of the base end and the combustion gas flows. In the elastic ring of the combustor that is disposed between the outer peripheral side of the tip end portion of the cylinder and the inner peripheral side of the base end portion of the second cylinder and allows displacement of the second cylinder relative to the first cylinder,
A cylindrical fixing portion that is fixed in contact with the first cylinder, is formed integrally with said fixing portion extends in a direction having the axial component of the fixed part has a contact portion before SL in contact with the second cylinder includes a spring portion, the spring portion, along the the reference to circumferential the axis of the plurality of slits Ru extending in axial direction comprises a position of the contact portion is the first cylinder in the axial direction formed The circumferential width of the spring portion between two slits adjacent in the circumferential direction among the plurality of slits is the widest at the position of the contact portion among the positions in the axial direction. Features.

  The elastic ring does not have a sealing function to reduce the air passing therethrough as much as possible.By forming the slit and actively passing the air, the slit width is set to a predetermined width, so that the air passing through the elastic ring is reduced. The target flow rate is adjusted. Moreover, in the elastic ring, since the circumferential width of the slit is uniform in the axial direction, even if the second cylinder is relatively displaced with respect to the first cylinder, the flow rate of air passing through the slit is substantially equal to the target flow rate. Can be maintained.

  Moreover, in the said elastic ring, a 2nd cylinder can be supported so that relative displacement is possible with respect to a 1st cylinder. That is, the elastic ring has a function of adjusting the flow rate of air passing therethrough and a function of supporting the second cylinder so as to be relatively displaceable with respect to the first cylinder. For this reason, by using the said elastic ring, like the combustor of patent document 1 demonstrated previously, between the outer peripheral surface of the front-end | tip part of an inner cylinder, and the inner peripheral surface of the base end part of a tail cylinder There is no need to arrange a seal member in addition to the spring member. Therefore, the number of parts can be reduced by using the elastic ring. However, this effect does not limit the arrangement of another member other than the elastic ring between the outer peripheral surface of the distal end portion of the inner cylinder and the inner peripheral surface of the proximal end portion of the tail cylinder.

  Further, in any one of the elastic rings of the combustor described above, the first spring portion is on the side opposite to the fixed portion in the axial direction with respect to the first contact portion that is the contact portion. You may have a 2nd contact part which contact | connects the cylinder to which the said fixing | fixed part is contact-fixed among a cylinder and said 2nd cylinder.

  In the elastic ring, the radial load of the other cylinder received by the first contact portion is received by the fixed portion and the second contact portion located on both sides in the axial direction with respect to the first contact portion. That is, the elastic ring is a double-sided support. Therefore, the elastic ring can reinforce the function of supporting the other cylinder so as to be displaceable with respect to the one cylinder.

A combustor as one aspect according to the invention for achieving the above object is as follows:
One of the elastic rings described above, the first cylinder and the second cylinder, and a nozzle that injects fuel into an inner peripheral side of the first cylinder or an inner peripheral side of the second cylinder. It is characterized by.

  Since the combustor also includes any one of the elastic rings described above, the flow rate of the air flowing between the outer peripheral side of the distal end portion of the first cylinder and the inner peripheral side of the proximal end portion of the second cylinder is adjusted. And the number of parts can be reduced.

  Here, in the combustor, the fixing portion of the elastic ring may be arranged on the one side in the axial direction of the first cylinder with respect to the spring portion of the elastic ring.

  Further, in any one of the above combustors, the second cylinder has a base end portion at a position on the one side in the axial direction from a portion where the elastic ring contacts, and from the outer peripheral side. A through hole penetrating to the inner peripheral side may be formed.

  In the combustor, the gas flows out from between the outer peripheral side of the distal end of the first cylinder and the inner peripheral side of the base end of the second cylinder to the inner peripheral side of the second cylinder and downstream of the first cylinder. The flow rate of air can be increased.

A gas turbine as one aspect according to the invention for achieving the above object is as follows:
One of the above combustors, and a turbine driven by the combustion gas from the second cylinder of the combustor are provided.
Moreover, the manufacturing method of the elastic ring as one aspect | mode which concerns on the invention for achieving the said objective is as follows.
A combustor comprising: a first cylinder; and a second cylinder in which a distal end, which is one side in the axial direction of the first cylinder, is inserted on the inner peripheral side of the base end and the combustion gas flows. Manufacture of an elastic ring for a combustor that is disposed between an outer peripheral side of the distal end portion of the cylinder and an inner peripheral side of the proximal end portion of the second cylinder and allows displacement of the second cylinder relative to the first cylinder In the method, a first intermediate cylinder made of metal is plastically processed, and a cylindrical fixing portion that is fixed in contact with one of the first cylinder and the second cylinder, and from the fixing section A second intermediate cylinder is formed that includes a spring portion extending in a direction having the axial component of the first intermediate cylinder and having a contact portion that contacts the other cylinder of the first cylinder and the second cylinder. And a width in the circumferential direction that includes the position of the contact portion in the axial direction of the second intermediate cylinder and extends in the axial direction and is based on the axis of the second intermediate cylinder A plurality of slits so as to be uniform in the axial direction and forming aligned in the circumferential direction.

  In the present invention, the flow rate of the air flowing between the outer peripheral side of the first cylinder and the inner peripheral side of the second cylinder in the combustor can be adjusted appropriately.

It is a principal part notched side view of the gas turbine in one Embodiment which concerns on this invention. It is a principal part notch whole side surface of the combustor in 1st embodiment which concerns on this invention. It is a principal part notched side view of the combustor in 1st embodiment which concerns on this invention. It is principal part sectional drawing of the inner cylinder, tail cylinder, and elastic ring in 1st embodiment which concerns on this invention. It is the whole elastic ring side view in a first embodiment concerning the present invention. It is the whole elastic ring front view in a first embodiment concerning the present invention. It is explanatory drawing which shows the manufacturing procedure of the elastic ring in 1st embodiment which concerns on this invention. It is explanatory drawing which shows the manufacture procedure of the elastic ring as a comparative example. It is explanatory drawing which shows the behavior of the elastic ring in 1st embodiment which concerns on this invention. It is explanatory drawing which shows the behavior of the elastic ring as a comparative example. It is a principal part notched side view of the combustor in 2nd embodiment which concerns on this invention. It is principal part sectional drawing of the inner cylinder, tail cylinder, and elastic ring in the modification of 1st embodiment which concerns on this invention.

  Hereinafter, embodiments of an elastic ring, a combustor including the elastic ring, and a gas turbine according to the present invention will be described in detail with reference to the drawings.

"Embodiment of gas turbine"
The gas turbine of this embodiment will be described with reference to FIG.

  The gas turbine of the present embodiment includes a compressor 1 that compresses air, a plurality of combustors 10 that generate combustion gas by burning fuel in the air from the compressor, a turbine 3 that is driven by the combustion gas, It has.

  The turbine 3 includes a turbine rotor 4 that rotates about a rotation axis Ar, and a turbine casing 7 that rotatably accommodates the turbine rotor 4. The turbine rotor 4 is connected to, for example, a generator (not shown) that generates electric power by the rotation of the turbine rotor 4. The turbine rotor 4 includes a rotor shaft portion 5 centering on the rotation axis Ar and extending in an axial direction parallel to the rotation axis Ar, and a plurality of blades fixed to the outer periphery of the rotor shaft portion 5 along the axial direction. Row 6. Each of the blade rows 6 has a plurality of blades 6a that are fixed to the rotor shaft portion 5 side by side in the circumferential direction with the rotation axis Ar as a reference.

  A gas flow path 9 through which combustion gas from the combustor 10 flows is formed between the inner peripheral side of the turbine casing 7 and the outer peripheral side of the rotor shaft portion 5. A stationary blade row 8 is disposed on the inner peripheral side of the turbine casing 7 and on the upstream side of each of the plurality of blade rows 6. Each of the stationary blade rows 8 has a plurality of stationary blades 8a that are fixed to the inner peripheral surface of the turbine casing 7 along the circumferential direction with the rotation axis Ar as a reference.

  The plurality of combustors 10 are fixed to the turbine casing 7 at equal intervals in the circumferential direction around the rotation axis Ar of the turbine rotor 4.

“First embodiment of combustor and elastic ring”
Next, a first embodiment of the combustor 10 included in the gas turbine described above and the elastic ring included in the combustor 10 will be described with reference to FIGS.

  As shown in FIG. 2, the combustor 10 of the present embodiment is arranged in the outer cylinder 19 fixed to the turbine casing 7 and the turbine casing 7, and the high-temperature and high-pressure combustion gas G is supplied to the gas flow of the turbine 3. A transition piece 11 to be sent to the path 9 and a fuel supply device 20 for supplying fuels Fm, Fp and air A into the transition piece 11 are provided.

  As shown in FIGS. 2 and 3, the fuel supplier 20 includes an inner cylinder 21, a pilot nozzle 25 disposed on the axis Ac of the inner cylinder 21, and an equal interval in the circumferential direction around the pilot nozzle 25. And a nozzle mounting base 27 to which the pilot nozzle 25 and the plurality of main nozzles 26 are attached.

  Here, the direction in which the axial line Ac of the inner cylinder 21 extends is the axial direction Da, the circumferential direction based on the axial line Ac is simply the circumferential direction Dc, and the radial direction based on the axial line Ac is simply the radial direction Dr. . In addition, the radial direction Dr and the side away from the axis Ac is the radially outer side, and the opposite side is the radially inner side. Furthermore, in the axial direction Da, the side where the tail cylinder 11 is present with respect to the fuel supplier 20 is the downstream side, and the opposite side is the upstream side.

  The nozzle mounting base 27 is fixed at a position on the most upstream side of the outer cylinder 19. The base end portion, which is the upstream portion of each nozzle 25, 26, is fixed to this nozzle mounting base 27. The pilot nozzle 25 injects the pilot fuel Fp from the tip portion, which is the downstream portion, to the downstream side. This pilot fuel Fp forms a diffusion flame by combustion. The plurality of main nozzles 26 inject main fuel Fm. The main fuel Fm is mixed with the air A flowing downstream around the main nozzle 26 and becomes a part of the premixed gas. The main fuel Fm in this premixed gas forms a premixed flame by combustion.

  A distal end portion 22 that is a downstream portion of the inner cylinder 21 is inserted on the inner peripheral side of the proximal end portion 12 that is an upstream portion of the tail cylinder 11. Therefore, the inner diameter at the proximal end portion 12 of the tail cylinder 11 is larger than the outer diameter at the distal end portion 22 of the inner cylinder 21. A through hole 13 is formed in the base end portion 12 of the transition piece 11 so as to penetrate from the outer peripheral side to the inner peripheral side.

  The combustor 10 of the present embodiment is further disposed between the outer peripheral side of the distal end portion 22 of the inner cylinder 21 and the inner peripheral side of the proximal end portion 12 of the tail cylinder 11, and the tail cylinder 11 with respect to the inner cylinder 21. It is provided with an elastic ring 30 that supports the ring so as to be displaceable. In the combustor 10 of the present embodiment, the inner cylinder 21 is a first cylinder and the tail cylinder 11 is a second cylinder.

  As shown in FIGS. 4 to 6, the elastic ring 30 is formed integrally with the cylindrical fixing portion 31 that is in contact with and fixed to the inner cylinder 21 on the inner peripheral side, and extends axially from the fixing portion 31. And a spring portion 32 extending in the direction having the Da component. The spring portion 32 includes a first contact portion 33 that contacts the inner peripheral surface of the outer cylinder 11 and a second contact portion 34 that contacts the outer peripheral surface of the inner cylinder 21. Since both the fixing portion 31 and the second contact portion 34 are in contact with the outer peripheral surface of the distal end portion 22 of the inner cylinder 21, the inner diameter thereof is substantially the same as the outer diameter of the distal end portion 22 of the inner cylinder 21. On the other hand, since the first contact portion 33 is in contact with the inner peripheral surface of the transition piece 11, the outer diameter is larger than the outer diameters of the fixed portion 31 and the second contact portion 34. The elastic ring 30 has a fixed portion 31 located on the most downstream side, a first contact portion 33 located on the upstream side of the fixed portion 31 and radially outside, and on the upstream side of the first contact portion 33. Thus, the second contact portion 34 is located on the radially inner side.

A plurality of slits 35 penetrating in the radial direction Dr and extending in the axial direction Da are formed in the spring portion 32 at equal intervals in the circumferential direction Dc. The slit 35 is formed from the upstream portion to the downstream end position of the spring portion 32. Therefore, the slit 35 is formed at the same position in the axial direction Da with the first contact portion 33 and further at the same position in the axial direction Da with the second contact portion 34. In a state where the elastic ring 30 is not incorporated into the combustor 10, the width W ₀ of the circumferential direction Dc of the slit 35 is uniform in the axial direction Da. Thus, in this embodiment, since the width W _{0 in} the circumferential direction Dc of the slit 35 formed in the spring portion 32 is uniform in the axial direction Da, the distance between the two slits 35 and 35 adjacent in the circumferential direction Dc. The width in the circumferential direction of the spring portion 32 is the widest at the position of the first contact portion 33 at the outermost radial direction among the positions in the axial direction Da. Incidentally, simply referred to as the width _{W 0} of the slit 35 in the following width _{W 0} in the circumferential direction Dc of the slit 35.

The number of the plurality of slits 35 formed in the spring portion 32, the width W _{0 of} the slit 35, and the length of the slit 35 in the axial direction Da are determined by the air A flowing from one side to the other side in the axial direction Da of the elastic ring 30. It is determined according to the target flow rate.

  Next, a manufacturing procedure of the elastic ring 30 will be described with reference to FIG.

  As shown in FIG. 7A, a metal first intermediate cylinder 91 is formed. Next, as shown in FIG. 7B, a mold is arranged on the inner peripheral side and the outer peripheral side of the first intermediate cylinder 91, and the first intermediate cylinder 91 is pressed in the radial direction, that is, plastically processed. The second intermediate cylinder 92 including the fixing portion 31 and the spring portion 32 having the first contact portion 33 and the second contact portion 34 is formed.

Next, as shown in FIGS. 7C and 7D, a long notch is formed in the axial direction Das of the second intermediate cylinder 92 in the region substantially the same as the spring portion 32 in the axial direction Das of the second intermediate cylinder 92. The plurality of slits 35 are formed in the second intermediate cylinder 92. In forming a plurality of slits 35 to the second intermediate cylinder 92, a plurality of slits 35 such that the width W ₀ of the axis Acs of the second intermediate cylinder 92 with respect the circumferential direction Dcs becomes uniform in the axial direction Das They are formed side by side in the circumferential direction Dcs.

  Thus, the elastic ring 30 is completed. The axial line Acs, the axial direction Das, and the circumferential direction Dcs of the first intermediate cylinder 91 coincide with the axial line Acs, axial direction Das, and circumferential direction Dcs of the second intermediate cylinder 92, respectively. Further, the axial line Acs, the axial direction Das, and the circumferential direction Dcs of the second intermediate cylinder 92 are the axial line Ac, axial direction Da, and circumferential direction of the inner cylinder 21 when the completed elastic ring 30 is incorporated into the combustor 10. Each corresponds to Dc.

  Next, with reference to FIG. 8, the manufacturing procedure of the elastic ring 30x as a comparative example will be described.

  As shown in FIG. 8A, a metal first intermediate cylinder 91 is formed as in the case of FIG. Next, as shown in FIG. 8B, a plurality of long cuts 93x are made in the first intermediate cylinder 91 in the axial direction Das of the first intermediate cylinder 91 to form a second intermediate cylinder 92x. The number of notches 93x is the same as the number of slits 35x.

  Next, as shown in FIGS. 8B and 8C, molds are arranged on the inner peripheral side and the outer peripheral side of the second intermediate cylinder 92x, and the second intermediate cylinder 92x is pressed in the radial direction Drs. The fixed portion 31x and the spring portion 32x having the first contact portion 33x and the second contact portion 34x are formed by processing, that is, plastic processing. As described above, the elastic ring 30x is completed as a comparative example, and the cut 93x that is made first becomes the slit 35x.

As described above, the elastic ring 30x of the comparative example is plastically processed in the radial direction Drs after the notch 93x to be the slit 35x is made in the first intermediate cylinder 91. During this plastic working, the portion that becomes the second contact portion 34x in the second intermediate tube 92x and the portion that becomes the fixed portion 31x in the second intermediate tube 92x have a slight amount of plastic deformation outward in the radial direction. . On the other hand, in this plastic working, the portion that becomes the first contact portion 33x in the second intermediate cylinder 92x has a large amount of plastic deformation outward in the radial direction. By this plastic working, the outer diameter of the first contact portion 33x becomes larger than the outer diameters of the fixed portion 31x and the second contact portion 34x. Therefore, the width _{W 2} of the slit 35x in the width _{W 2,} and the fixed portion 31x side at the same position in the second contact portion 34x and the axial Das slit 35x in the resilient ring 30x is formed on the first intermediate cylinder 91 The width of the cut 93x is almost the same and narrow. On the other hand, the width _{W 1} at the same position in the first contact portion 33x and the axial Das slit 35x in the resilient ring 30x is much greater than the width _{W 2} of the first contact portion 33x and the fixed portion 31x side of the slit 35x wide.

Therefore, in the elastic ring 30x of the comparative example, the width of the slit 35x is different at each position in the axial direction Das. Specifically, the elastic ring 30x of the comparative example, the width W ₂ of the slit 35x at both axial ends Das is narrower than the width W ₀ of the slit 35 of the present embodiment is the intermediate portion of the axial Das the width _{W 1} of the slit 35x in the first contact portion 33x is wider than the width _{W 0} of the slit 35 of the present embodiment.

Therefore, when the elastic ring 30 in which the width W ₀ of the circumferential direction Dc of the slit 35 is uniform in the axial direction Da is manufactured, it is preferable to manufacture by the method described with reference to FIG.

  As shown in FIGS. 3 and 4, the completed elastic ring 30 of the present embodiment is arranged such that the fixing portion 31 is on the downstream side with respect to the second contact portion 34 on the outer peripheral side of the distal end portion 22 of the inner cylinder 21. And put on. Then, the fixing portion 31 of the elastic ring 30 is welded to the outer peripheral surface of the distal end portion 22 of the inner cylinder 21, and the elastic ring 30 is contacted and fixed to the inner cylinder 21.

  When the elastic ring 30 is fixed to the distal end portion 22 of the inner cylinder 21, the distal end portion 22 of the inner cylinder 21 is inserted into the inner peripheral side of the proximal end portion 12 of the tail cylinder 11 together with the elastic ring 30. As a result, the first contact portion 33 of the elastic ring 30 comes into contact with the inner peripheral surface of the proximal end portion 12 of the tail tube 11, and the second contact portion 34 of the elastic ring 30 contacts the outer peripheral surface of the distal end portion 22 of the inner tube 21. Contact.

  During the operation of the gas turbine, the combustor 10 receives the fuels Fm and Fp from the fuel supply source and the air A from the compressor 1 and receives the fuels Fm and Fp as described above with reference to FIGS. Is burned in the air A to generate combustion gas G.

  Specifically, pilot fuel Fp is supplied to the pilot nozzle 25. The pilot fuel Fp is ejected from the front end of the pilot nozzle 25 toward the inner peripheral side of the transition piece 11 toward the downstream side. Further, the air A from the compressor 1 passes through the inner peripheral side of the inner cylinder 21 and is sent into the tail cylinder 11. The pilot fuel Fp ejected into the transition piece 11 is combusted in the air A sent into the transition piece 11 to form a diffusion flame.

  Main fuel Fm is supplied to the main nozzle 26. The main fuel Fm is ejected from the main nozzle 26 in the inner cylinder 21. Air A from the compressor 1 is supplied around the main nozzle 26 and mixed with the main fuel Fp from the main nozzle 26. The mixed gas of the air A and the main fuel Fm flows from the inner cylinder 21 into the tail cylinder 11 and combusts here to form a premixed flame.

  The combustion gas G formed by the combustion of the fuels Fm and Fp flows downstream in the tail cylinder 11 and flows into the gas flow path 9 of the turbine 3.

  As shown in FIG. 4, the air A from the compressor 1 also flows between the inner peripheral side of the most downstream end of the tail cylinder 11 and the outer peripheral surface of the inner cylinder 21. This air A is between the inner peripheral surface of the base end portion 12 of the tail cylinder 11 and the outer peripheral surface of the distal end portion 22 of the inner cylinder 21 and passes through the plurality of slits 35 of the elastic ring 30. As described above, the flow rate of the air A passing through the plurality of slits 35 is substantially the target flow rate.

  Between the inner peripheral surface of the base end portion 12 of the tail tube 11 and the outer peripheral surface of the distal end portion 22 of the inner tube 21, in the region downstream of the elastic ring 30, the outer periphery side of the tail tube 11 is further provided. The air A from the compressor 1 flows in through the through hole 13 of the tail cylinder 11.

  The air A that has passed through the plurality of slits 35 of the elastic ring 30 and the air A that has passed through the through-hole 13 of the tail cylinder 11 are both the outer peripheral side of the most downstream end of the inner cylinder 21 and the inner peripheral surface of the tail cylinder 11. It passes through the gap between them and flows out in the tail cylinder 11 and downstream of the inner cylinder 21. A part of the air A flows along the inner peripheral surface of the tail cylinder 11 in which the fuel burns, and the inner peripheral surface of the tail cylinder 11 is film-cooled to suppress burning of the tail cylinder 11. The remaining part of the air A is used as combustion air when forming a premixed flame.

  As described above, the elastic ring 30 has a function of flowing air A having a target flow rate between the inner peripheral surface of the base end portion 12 of the tail cylinder 11 and the outer peripheral surface of the distal end portion 22 of the inner cylinder 21. . Further, the elastic ring 30 also has a function of supporting the tail cylinder 11 so as to be displaceable with respect to the inner cylinder 21. That is, the elastic ring 30 of the present embodiment has a function of adjusting the air flow rate and a function of supporting the tail cylinder 11 so as to be displaceable.

  Here, with reference to FIG.9 and FIG.10, the behavior of the elastic rings 30 and 30x when the transition piece 11 is displaced to the radial direction outer side with respect to the inner cylinder 21 is demonstrated. 9 is a view of the elastic ring 30 of the present embodiment as viewed from the upstream side, and FIG. 10 is a view of the elastic ring 30x of the comparative example as viewed from the upstream side.

As shown in FIG. 9, when the transition piece 11 is displaced outward in the radial direction Dr with respect to the inner cylinder 21, the spring portion 32 of the elastic ring 30 of the present embodiment is elastically deformed following this displacement, and the spring portion. The first contact portion 32 of 32 is displaced radially outward, and the second contact portion 34 of the spring portion 32 is displaced downstream. For this reason, the radius of the elastic ring 30 at the position in the axial direction Da where the first contact portion 33 exists increases, and the width W ₀₁ of the slit 35 at this position increases. That is, when the tail tube 11 relative to the inner cylinder 21 is displaced radially outwardly, the width W ₀ of the slit at the position in the axial direction Da in which the fixing portion 31 and the second contact portion 34 exists, substantially unchanged although not, the width of the slit 35 at the same position in the first contact portion 33 and the axial direction Da is spread from a width W ₀ in the width W _01.

  Therefore, when the transition piece 11 is displaced in the radial direction Dr with respect to the inner cylinder 21, the flow rate of the air A passing through the slit 35 of the elastic ring 30 slightly changes.

Further, as shown in FIG. 10, even when the elastic ring 30x of the comparative example is used, when the tail cylinder 11 is displaced radially outward with respect to the inner cylinder 21, the spring portion 32x of the elastic ring 30x is subjected to this displacement. Following the elastic deformation, the first contact portion 33x of the spring portion 32x is displaced radially outward, and the second contact portion 34x of the spring portion 32x is displaced downstream. For this reason, also in the elastic ring 30x of the comparative example, when the tail cylinder 11 is displaced radially outward with respect to the inner cylinder 21, as in the case of the elastic ring 30 of the present embodiment, the fixed portion 31x and the second contact portion the width W ₂ of the slit 35x at the position of the axial direction Da of 34x is present, but does not substantially change, the width of the width W ₁ of the slit 35x at the position of the axial direction Da in which the first contact portion 33x is present spread to the width _{W 11.}

In the elastic ring 30x of the comparative example, even prior to incorporation into the combustor, the width W ₂ of the slit 35x at the position of the axial direction Da in which the fixing portion 31x and the second contact portion 34x is present, as described above, the combustor 10 It is narrower than the width W ₀ of the slit 35 in the elastic ring 30 of this embodiment before being incorporated into the ring. Further, the elastic ring 30x of the comparative example, even prior to incorporation into the combustor, the width W ₁ of the slit 35x at the position of the axial direction Da is present radially outside of the first contact portion 33x, as described above, the combustion It is wider than the width W ₀ of the slit 35 in the elastic ring 30 of this embodiment before being incorporated in the vessel 10. Therefore, the flow rate of the air A passes through the slit 35x of the elastic ring 30x of the comparative example will be unevenly distributed radially outward the width W ₁ of the slit 35x is wide. Moreover, as described above, when the transition piece 11 is displaced radially outward with respect to the inner cylinder 21, the flow rate of the air A passing through the slit 35x of the elastic ring 30x of the comparative example is more unevenly distributed radially outward. .

  For this reason, in the elastic ring 30x of the comparative example, the flow rate change of the air A passing through the slit 35x before and after the displacement of the transition piece 11 is larger than that of the elastic ring 30 of the present embodiment. In other words, in the elastic ring 30 of the present embodiment, the flow rate change of the air A passing through the slit 35 before and after the displacement of the transition piece 11 is smaller than that of the elastic ring 30x of the comparative example. Therefore, in the present embodiment, even if the transition piece 11 is displaced with respect to the inner cylinder 21, the flow rate of the air A passing through the slit 35 can be substantially maintained at the target flow rate.

  As described above, the elastic ring 30 according to the present embodiment does not have a sealing function for reducing the amount of air A passing as much as possible. By setting the predetermined width W0, the air A passing through the elastic ring 30 is adjusted to the target flow rate. In addition, in the present embodiment, as described above, the width W0 of the slit 35 is uniform in the axial direction Da, so that even if the transition piece 11 is displaced with respect to the inner cylinder 21, the air A passing through the slit 35 is displaced. The flow rate can be almost maintained at the target flow rate.

  Since the elastic ring 30 of the present embodiment has a function of adjusting the air flow rate in addition to the function of supporting the transition piece 11 so as to be displaceable, it is like the combustor described in Patent Document 1 described above. In addition, there is no need to dispose a seal member in addition to the spring member between the outer peripheral surface of the distal end portion of the inner cylinder and the inner peripheral surface of the proximal end portion of the tail cylinder. Therefore, in this embodiment, the number of parts can be reduced. However, this effect is that, in this embodiment, another member other than the elastic ring 30 is arranged between the outer peripheral surface of the distal end portion 22 of the inner cylinder 21 and the inner peripheral surface of the proximal end portion 12 of the tail cylinder 11. It does not limit that.

"Second embodiment of combustor and elastic ring"
Next, a second embodiment of the combustor included in the gas turbine described above and the elastic ring included in the combustor will be described with reference to FIG.

  Similarly to the combustor 10 of the first embodiment, the combustor 10a of the present embodiment also includes a fuel supply device 20 and a tail cylinder 11a that sends the high-temperature / high-pressure combustion gas G to the gas flow path of the turbine. Yes. The transition piece 11a is disposed on the downstream side of the inner cylinder 21 of the fuel supply device 20 in the same manner as the transition piece 11 of the first embodiment. However, the combustor 10a of the present embodiment further includes a combustion cylinder 41, which is disposed on the downstream side of the inner cylinder 21, and the tail cylinder 11a is disposed on the downstream side of the combustion cylinder 41. .

  The distal end portion 22 of the inner cylinder 21 is inserted on the inner peripheral side of the proximal end portion 43 of the combustion cylinder 41. Moreover, the front-end | tip part 42 of the combustion cylinder 41 is inserted in the inner peripheral side of the base end part 12a of the tail cylinder 11a. Therefore, the inner diameter at the proximal end 43 of the combustion cylinder 41 is larger than the outer diameter at the distal end 22 of the inner cylinder 21, and the inner diameter at the proximal end 12 a of the tail cylinder 11 a is the outer diameter at the distal end 42 of the combustion cylinder 41. Bigger than.

  The combustor 10a of the present embodiment is further disposed between the outer peripheral side of the distal end portion 42 of the combustion cylinder 41 as the first cylinder and the inner peripheral side of the base end part 12a of the tail cylinder 11a as the second cylinder. In addition, an elastic ring 30a for supporting the tail cylinder 11a so as to be displaceable with respect to the combustion cylinder 41 is provided.

  The basic configuration of the elastic ring 30a is the same as the basic configuration of the first embodiment. That is, the elastic ring 30a of the present embodiment is not clearly depicted in FIG. 11, but is a fixed portion that is fixed in contact with the combustion cylinder 41 as the first cylinder, and a direction having an axial Da component from the fixed section. And a spring portion extending in the direction. The spring part has a first contact part that contacts the inner peripheral surface of the tail cylinder 11a as the second cylinder, and a second contact part that contacts the outer peripheral surface of the combustion cylinder 41 as the first cylinder. The spring portion is formed with a plurality of slits extending in the radial direction and extending in the axial direction and having a uniform width in the axial direction and arranged in the circumferential direction.

  However, in the present embodiment, the air A that has passed through the slit of the elastic ring 30a is exclusively used as film cooling air that cools the inner peripheral surface of the tail cylinder 11a. Therefore, in this embodiment, the target flow rate of the air A that passes through the slit is different from that of the first embodiment. For this reason, the length in the axial direction of the slit and the width of the slit of this embodiment are different from those of the first embodiment.

  As described above, the elastic ring 30a of the present embodiment also has the same effects as the first embodiment because the basic configuration is the same as that of the elastic ring 30 of the first embodiment.

“Modification of elastic ring”
Next, a modification of the elastic ring in the first embodiment will be described with reference to FIG.

Similar to the elastic ring 30 of the first embodiment, the elastic ring 30b of the present modification includes a fixing portion 31b that is fixed in contact with the inner cylinder 21, and a spring portion 32b that extends from the fixing portion 31b in a direction having an axial Da component. ,have. The spring portion 32 b has a first contact portion 33 b that contacts the inner peripheral surface of the transition piece 11. In addition, the spring portion 32b, extending in the axial direction Da penetrate radially Dr, the width W ₀ is formed in parallel a plurality of slits 35b is uniform in the axial direction Da in the circumferential direction Dc. However, the spring part 32b in the elastic ring 30b of this modification does not have a portion extending downstream from the first contact part 33b, that is, does not have the second contact part 34 in the first embodiment.

Above, the elastic ring 30b of this modification also, extending in a direction having a component in the axial direction Da, the width W ₀ is uniform slit 35b in the axial direction Da is formed, the elastic ring 30 of the first embodiment There are basically the same effects.

  By the way, the elastic ring 30 of 1st embodiment is located in the both sides of the axial direction Da on the basis of the 1st contact part 33 with respect to the load of the radial direction Dr of the tail cylinder 11 received by the 1st contact part 33. It is received by the fixed portion 31 and the second contact portion 34. That is, the elastic ring 30 of the first embodiment is a double-sided support. On the other hand, the elastic ring 30b of this modification fixes the load in the radial direction Dr of the tail cylinder 11 received by the first contact portion 33b because the second contact portion 34 in the first embodiment is not provided. It is received only by the part 31b. That is, the elastic ring 30b of this modification is cantilever support. Therefore, the elastic ring 30b of the present modification is somewhat inferior to the elastic ring 30 of the first embodiment from the functional surface that supports the transition of the tail cylinder 11 with respect to the inner cylinder 21. However, since the elastic ring 30b of this modification has a simpler shape than the elastic ring 30 of the first embodiment, the manufacturing cost can be reduced more than the elastic ring 30 of the first embodiment.

  In addition, although this modification was demonstrated as a modification of the elastic ring 30 of 1st embodiment here, you may deform | transform the elastic ring 30b of 2nd embodiment similarly to this modification.

  In each of the above embodiments and modifications, the elastic ring is fixed to the first cylinder on the upstream side of the second cylinder, but the elastic ring may be fixed to the second cylinder. In this case, the first contact portion of the elastic ring comes into contact with the outer peripheral surface of the first cylinder.

  1: compressor 1, 3: turbine, 4: turbine rotor, 6a: moving blade, 7: turbine casing, 8a: stationary blade, 9: gas flow path, 10, 10b: combustor, 11, 11a: tail cylinder ( (Second cylinder), 12, 12a: proximal end (of the tail cylinder), 13: through hole, 19: outer cylinder, 20: fuel feeder, 21: inner cylinder (first cylinder), 22: (inner cylinder) ) Tip portion, 30, 30a, 30b: elastic ring, 31, 31b: fixed portion, 32, 32b: spring portion, 33, 33b: first contact portion, 34: second contact portion, 35, 35b: slit, 41 : Combustion cylinder (first cylinder), 42: tip of (combustion cylinder), 91: first intermediate cylinder, 92: second intermediate cylinder

Claims (7)

A combustor comprising: a first cylinder; and a second cylinder in which a distal end, which is one side in the axial direction of the first cylinder, is inserted on the inner peripheral side of the base end and the combustion gas flows. In the elastic ring of the combustor that is disposed between the outer peripheral side of the tip end portion of the cylinder and the inner peripheral side of the base end portion of the second cylinder and allows displacement of the second cylinder relative to the first cylinder,
A cylindrical fixing portion fixed in contact with the first cylinder;
A spring part formed integrally with the fixed part, extending from the fixed part in a direction having the axial component, and having a contact part in contact with the second cylinder;
With
Wherein the spring portion is formed parallel to the plurality of slits in the circumferential direction relative to the axis of said first tube extending in axial direction comprises a position of the contact portion in the axial direction,
The circumferential width of the spring portion between two slits adjacent in the circumferential direction among the plurality of slits is the widest at the position of the contact portion among the positions in the axial direction.
An elastic ring of a combustor characterized by that. The elastic ring of the combustor according to claim 1 ,
The spring portion is in contact with the fixed portion between the first tube and the second tube on the side opposite to the fixed portion in the axial direction with respect to the first contact portion that is the contact portion. Having a second contact portion in contact with the cylinder to be fixed,
An elastic ring of a combustor characterized by that. The elastic ring of the combustor according to claim 1 or 2 ,
The first cylinder and the second cylinder;
A nozzle for injecting fuel into an inner peripheral side of the first cylinder or an inner peripheral side of the second cylinder;
A combustor comprising: The combustor according to claim 3 .
The fixing portion of the elastic ring is disposed on the one side in the axial direction of the first cylinder with respect to the spring portion of the elastic ring.
Combustor characterized by that. The combustor according to claim 3 or claim 4 ,
The second cylinder is formed with a through hole penetrating from the outer peripheral side to the inner peripheral side at a position on the one side in the axial direction with respect to the base end portion and a portion with which the elastic ring contacts. Yes,
Combustor characterized by that. A combustor according to any one of claims 3 to 5 ,
A turbine driven by the combustion gas from the second cylinder of the combustor;
A gas turbine comprising: A combustor comprising: a first cylinder; and a second cylinder in which a distal end, which is one side in the axial direction of the first cylinder, is inserted on the inner peripheral side of the base end and the combustion gas flows. Manufacture of an elastic ring for a combustor that is disposed between an outer peripheral side of the distal end portion of the cylinder and an inner peripheral side of the proximal end portion of the second cylinder and allows displacement of the second cylinder relative to the first cylinder In the method
A first intermediate cylinder made of metal is plastically processed, and a cylindrical fixing part that is fixed in contact with one of the first cylinder and the second cylinder; Forming a second intermediate cylinder that includes a spring portion extending in a direction having an axial component of the intermediate cylinder and having a contact portion in contact with the other cylinder of the first cylinder and the second cylinder;
A plurality of slits including the position of the contact portion in the axial direction of the second intermediate cylinder, extending in the axial direction, and having a uniform circumferential width with respect to the axis of the second intermediate cylinder in the axial direction Formed side by side in the circumferential direction,
A method of manufacturing an elastic ring for a combustor.

Images