JP6787005B2 - Liner for combustion equipment - Google Patents

Description

The present invention relates to a liner used in a combustion device.

An aircraft engine, which is a combustion device, is equipped with a combustor. The combustor burns fuel to produce high temperature gas. Therefore, a corrugated liner as a heat shield is used to protect the engine components located around the combustor from the hot gas. For example, Patent Document 1 discloses a corrugated liner used in an aircraft engine.

Japanese Unexamined Patent Publication No. 2003-329245

The liner disclosed in Patent Document 1 has a tubular shape, and a high-temperature gas flows inside the liner. Then, the liner takes in a low-temperature gas such as compressed air from around the liner through the cooling holes into the liner, and cools the inner surface of the liner in contact with the high-temperature gas.

In recent years, from the viewpoint of improving the performance of the combustor, the temperature of the high-temperature gas generated in the combustor tends to increase. On the other hand, the amount of cold gas that can be used to cool the liner is limited. Therefore, a technique that can efficiently use the low temperature gas for cooling the liner is desired.

The liner for a combustion device according to an embodiment of the present invention has a first flow path through which a first gas containing a first temperature flows and a second gas containing a second temperature lower than the first temperature. A liner body that separates the second flowing flow path is provided. A plurality of liner bodies are provided in the first direction so as to extend in the second direction intersecting the first direction in which the first gas and the second gas flow and project toward the first flow path side. A second apex and a second apex that extend in the second direction and are provided between the first apex in the first direction so as to project toward the first flow path side with the first apex. A first valley provided between the first apex and a second apex adjacent to the downstream side of the first apex in the first direction while extending to the second flow path side. In the first slope portion and the first slope portion formed between the portion and the first top portion in the first direction and the first valley portion adjacent to the downstream side with respect to the first top portion. It includes a first cooling hole provided on a first axis extending in a first direction and communicating the first flow path and the second flow path.

The first cooling hole is provided on the first slope portion. The first slope portion is provided between the first top portion and the first valley portion. Further, the first valley portion is provided between the first top and the second top. Therefore, the second top is provided on the downstream side of the first cooling hole. Further, the second gas ejected from the first cooling hole located upstream of the second top forms a vortex that rotates around the first direction while flowing along the first direction. .. This vortex excites a part of the first gas to flow toward the surface of the liner body. Here, the flow toward the surface of the liner body generated in a part of the first gas is obstructed by the second top protruding toward the first flow path side. Therefore, it becomes difficult for the first gas caught in the vortex rotating around the first direction to flow under the vortex. As a result, the liner main body can be efficiently cooled by the second gas ejected from the first cooling hole. Therefore, the second gas can be efficiently used for cooling the liner main body.

A second slope formed between the first valley and a second top adjacent to the first valley downstream of the first valley in the first direction, and a first in the second slope. It may further include a second cooling hole provided on a second axis extending in the direction of the above and communicating the first flow path and the second flow path. In this combustion device liner, since the first cooling hole is provided on the first slope portion, the second gas ejected from the first cooling hole has the same velocity component as the first direction. .. Therefore, the second slope portion and the second top portion existing on the downstream side of the first cooling hole can be cooled. On the other hand, the second cooling hole is provided on the second slope portion. The second gas ejected from the second cooling hole has a velocity component in the direction opposite to the first direction. Therefore, the first slope portion and the first top portion existing on the upstream side of the second cooling hole can be cooled. Therefore, the second gas can be efficiently used for cooling the liner main body.

It extends in the second direction, projects toward the second flow path side, and is provided between the second top and the first top adjacent to the downstream side of the second top in the first direction. The second valley may be further included. According to this configuration, a circulating flow by the second gas can be preferably generated between the surface of the liner main body and the main stream through which the first gas flows between the first tops. Therefore, the second gas can be used more efficiently for cooling the liner body.

According to the present invention, there is provided a liner for a combustion device that can efficiently use a low temperature gas for cooling the liner.

FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine provided with a liner for a combustion device according to the present embodiment. FIG. 2 is an enlarged perspective view showing a part of the liner main body. FIG. 3 is a cross-sectional view of a part of the liner main body. FIG. 4 is a diagram for defining the waveform shape of the liner main body. Part (a) of FIG. 5 is a contour diagram showing the result of Comparative Example 1 showing the temperature distribution on the surface of the liner main body, and part (b) of FIG. 5 is an example showing the temperature distribution on the surface of the liner main body. It is a contour figure which shows the result of 1. FIG. 6 is a graph showing the film cooling efficiency along the first direction. The parts (a), (b) and (c) of FIG. 7 are contour diagrams showing the three-dimensional temperature distribution on the liner main body shown in the part (a) of FIG. The parts (a), (b) and (c) of FIG. 8 are contour diagrams showing the three-dimensional temperature distribution on the liner body shown in the part (b) of FIG. FIG. 9 shows the results of Comparative Example 3 showing the first streamline and the second streamline on the liner body. FIG. 10 shows the results of Example 3 showing the first streamline and the second streamline on the liner body.

Hereinafter, embodiments for carrying out the present invention will be described in detail with reference to the accompanying drawings. In the description of the drawings, the same elements are designated by the same reference numerals, and duplicate description will be omitted.

FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine 10 provided with a liner for a combustion device (hereinafter, also simply referred to as “liner”) according to the present embodiment. The jet engine 10 includes a fan 11, a compressor 12, a combustor 13, and a turbine 14.

The fan 11 is for taking in outside air inside the jet engine 10, and is provided around the rotation shaft A of the rotation-driven shaft portion 16. The fan 11 is provided on the upstream side of the compressor 12. The compressor 12 compresses the air taken in by the fan 11 to form compressed air A2 (second gas). The compressor 12 has a configuration in which rotating blades 11a and fixed stationary blades 11b are alternately arranged in a plurality of stages in the air flow direction. The combustor 13 burns the air compressed by the compressor 12 together with the fuel, and includes a fuel supply mechanism and an ignition device. The turbine 14 converts a part of the velocity energy of the combustion gas A1 (first gas) generated by burning air and fuel in the combustor 13 into rotational energy. The turbine 14 drives the fan 11 and the compressor 12 with the rotational energy. The compressor 12, the combustor 13, and the turbine 14 are provided between the inner housing 15a and the shaft portion 16. Further, on the outer peripheral side of the fan 11, an outer housing 15b is provided so as to surround the fan 11, the shaft portion 16 and the inner housing 15a. The outer housing 15b is connected to the inner housing 15a via a stationary blade 11b.

In the jet engine 10 having such a configuration, air is taken into the inside of the jet engine 10 by the fan 11. Then, a part of the air flows between the inner housing 15a and the shaft portion 16 and is supplied to the compressor 12. Further, the other part of the air taken in by the fan 11 flows between the outer housing 15b and the inner housing 15a. The air supplied to the compressor 12 is compressed by the compressor 12 and then burned together with the fuel in the combustor 13. Then, a part of the velocity energy of the combustion gas generated by combustion is converted into rotational energy by the turbine 14 and used for driving the fan 11 and the compressor 12. On the other hand, the remaining velocity energy of the combustion gas is used to give propulsion to the jet engine 10 when the combustion gas is exhausted from the rear of the jet engine 10. As a result, the jet engine 10 propels. In this specification, the terms "upstream side" and "downstream side" are used with reference to the flow of air taken into the jet engine 10. Further, the terms "outer circumference side" and "inner circumference side" are used with reference to the rotation axis A.

The combustor 13 includes a case 21 and a combustion unit 22. The case 21 is a container that forms a space for burning a mixture of fuel and air, and forms a first flow path through which the combustion gas A1 flows. The case 21 is formed in an annular shape in the inner housing 15a so as to surround the shaft portion 16. A gap 31 is provided between the case 21 and the inner housing 15a. Further, a gap 32 is also provided between the case 21 and the shaft portion 16. These gaps 31 and 32 correspond to a second flow path through which the compressed air A2 flows.

A combustion unit 22 is provided on the upstream end side of the case 21. The combustion unit 22 includes, for example, a fuel supply mechanism and an ignition device. In the case 21, the liner main body 1 is provided on the downstream side of the combustion unit 22. The liner main body 1 separates a first flow path through which the combustion gas A1 flows and a second flow path through which the compressed air A2 flows. Therefore, the liner body 1 constitutes a part of the case 21. An opening 23 is provided on the downstream end side of the case 21, and the combustion gas A1 is discharged to the outside of the case 21.

In the combustor 13 having such a configuration, the air supplied from the compressor 12 and the fuel supplied from the fuel supply mechanism are mixed to form an air-fuel mixture. Then, the combustion gas A1 is formed by igniting the air-fuel mixture by the ignition device. The combustion gas A1 flows through the case 21 and is provided to the turbine 14 through the opening 23. Here, when the combustion gas A1 flows in the case 21, the inner surface of the case 21 is exposed to the high-temperature combustion gas A1. Further, a part of the compressed air A2 provided by the compressor 12 flows in the gap 31 between the case 21 and the inner housing 15a and the gap 32 between the case 21 and the shaft portion 16. The temperature of the compressed air A2 flowing in the gaps 31 and 32 is lower than that of the combustion gas A1. As an example, the temperature of the combustion gas A1 (first temperature) is about 2000 ° C., and the temperature of the compressed air A2 (second temperature) is about 500 ° C. Therefore, the compressed air A2 is taken into the case 21 by providing a plurality of cooling holes in the liner main body 1 of the case 21. The compressed air A2 forms a temperature boundary layer, which will be described later, between the high-temperature combustion gas A1 and the liner main body 1. This temperature boundary layer suppresses the direct exposure of the inner surface of the liner body 1 to the combustion gas A1. Therefore, the case 21 having the liner body 1 is thermally protected.

Next, the liner main body 1 will be described in detail. FIG. 2 is an enlarged perspective view showing a part of the liner main body 1. Further, FIG. 3 is a cross-sectional view of a part of the liner main body 1. As shown in FIGS. 2 and 3, the liner body 1 is a thin plate having a wavy cross section. The liner body 1 is made of a plate material such as a nickel-based heat-resistant alloy.

The liner body 1 includes a first top 2A, a second top 2B, a first valley 3A, a second valley 3B, a first slope 4, and a second slope 5. It has a third slope portion 6, a fourth slope portion 7, a first cooling hole 8, and a second cooling hole 9. In the liner main body 1, these portions are formed in this order along the first direction D1 (from upstream to downstream). Then, a plurality of configurations including these portions are repeatedly provided along the first direction D1. Therefore, when the liner body 1 is viewed in cross section, the liner body 1 has a so-called wavy shape.

The first top portion 2A is a portion protruding inward of the case 21. That is, the first top portion 2A projects toward the first flow path side through which the combustion gas A1 flows. The first top 2A extends in a second direction D2 that intersects the first direction D1 through which the combustion gas A1 and the compressed air A2 flow. Further, the first top portion 2A is repeatedly provided at a predetermined pitch along the first direction D1.

The second top 2B is a portion protruding inward of the case 21. That is, the second top 2B projects toward the first flow path side through which the combustion gas A1 flows, similarly to the first top 2A. One second top 2B is provided between the first tops 2A in the first direction D1.

The first valley portion 3A is a portion protruding toward the outside of the case 21. That is, the first valley portion 3A projects toward the second flow path side through which the compressed air A2 flows. The first valley portion 3A extends in the second direction D2, similarly to the first top portion 2A. In the first direction D1, one first valley portion 3A is provided between the first top portion 2A and the second top portion 2B.

The second valley portion 3B is a portion protruding toward the outside of the case 21. That is, the second valley portion 3B projects toward the second flow path side through which the compressed air A2 flows, similarly to the first valley portion 3A. The second valley portion 3B extends in the second direction D2, similarly to the first top portion 2A. One second valley 3B is provided between the second top 2B and the first top 2A in the first direction D1. In other words, between the first tops 2A, the second valley 3B is provided downstream of the first valley 3A.

The first slope portion 4 is formed between the first top portion 2A and the first valley portion 3A in the first direction D1. Therefore, the first slope portion 4 has a substantially constant negative inclination (downward slope) in the first direction D1.

The second slope portion 5 is formed between the first valley portion 3A and the second top portion 2B in the first direction D1. Specifically, the second slope portion 5 is provided on the downstream side of the first slope portion 4 via the first valley portion 3A. Therefore, the second slope portion 5 has a substantially constant positive inclination (upward slope) in the first direction D1.

The third slope portion 6 is formed between the second top portion 2B and the second valley portion 3B in the first direction D1. Specifically, the third slope portion 6 is provided on the downstream side of the second slope portion 5 via the second top portion 2B. Therefore, the third slope portion 6 has a substantially constant negative inclination (downward slope) in the first direction D1, similarly to the first slope portion 4.

The fourth slope portion 7 is formed between the second valley portion 3B and the first top portion 2A located on the downstream side of the second valley portion 3B in the first direction D1. Specifically, the fourth slope portion 7 is provided on the downstream side of the third slope portion 6 via the second valley portion 3B. Therefore, the fourth slope portion 7 has a substantially constant positive inclination (upward slope) in the first direction D1 like the second slope portion 5.

The wavy shape of the liner body 1 will be further described. FIG. 4 is a diagram for defining the waveform shape of the liner main body 1. As shown in FIG. 4, the distance S1 from the first top 2A to the next second top 2B is defined as the wavelength L. Then, the positions of the second top 2B, the first valley 3A, the second valley 3B, the first cooling hole 8, and the second cooling hole 9 in the first direction D1 are upstream. It is defined based on the distance from the first top 2A on the side. That is, the distance S2 is between the first top 2A and the second downstream top 2B. The distance S3 is between the first top 2A and the first valley 3A. The distance S4 is between the first top 2A and the second valley 3B.

The waveform shape of the liner body 1 can be defined with the wavelength L as the reference length. The ratio of the distance S2 from the first top 2A to the second top 2B to the wavelength L (distance S1) is 0.40 or more and 0.60 or less in (S2 / S1), and 0.49 as an example. is there. The ratio of the distance S3 from the first top 2A to the first valley 3A with respect to the wavelength L is (S3 / S1) of 0.20 or more and 0.30 or less, and is 0.25 as an example. The ratio of the distance S4 from the first top 2A to the second valley 3B with respect to the wavelength L is (S4 / S1) of 0.65 or more and 0.85 or less, and 0.74 as an example.

Further, in the waveform shape of the liner main body 1, the distance T1 from the first top portion 2A to the second valley portion 3B in the third direction D3 is defined as the amplitude (2r). Assuming a center line passing through the center of the distance from the first top 2A to the second valley 3B, the distance from the first top 2A to the center line is defined as the amplitude (r), and the second valley The distance from the part 3B to the center line is defined as the amplitude (r). Further, in the waveform shape of the liner main body 1, the distance T2 is from the first top portion 2A to the first valley portion 3A in the third direction D3. The ratio (T2 / T1) of the distance T1 from the first top 2A to the second valley 3B in the third direction D3 and the distance T2 from the first top 2A to the first valley 3A is 0. It is .50 or more and 0.85 or less, and 0.67 as an example. This distance T2 is smaller than the distance T1 (amplitude 2r) from the first top 2A to the second valley 3B. That is, it can be said that the second valley portion 3B is deeper than the first valley portion 3A in the third direction D3 with respect to the first top portion 2A. Then, in the waveform shape of the liner main body 1, the distance T3 is from the first top 2A to the second top 2B in the third direction D3. The distance T3 is smaller than the distance T1 from the first top 2A to the second valley 3B and smaller than the distance T2 from the first top 2A to the first valley 3A.

Further, the distance S2 from the first top 2A to the second top 2B adjacent to the downstream side is to the first top 2A adjacent to the downstream side with respect to the second top 2B and the second top 2B. It is shorter than the distance S5. According to such a configuration, the second top 2B is closer to the first top 2A on the upstream side than the first top 2A on the downstream side. "The second top 2B is closer to the first top 2A on the upstream side than the first top 2A on the downstream side" means that the wavelength L (distance S1) and the first top 2A to the second top It can also be indicated by the distance S2 to 2B. For example, the ratio of the distance S1 to the wavelength L (S2 / S1) is 0.40 or more and 0.60 or less, and 0.49 as an example. According to the position of the second top portion 2B as described above, the inclination R of the first slope portion 4 with respect to the first direction D1 tends to increase. Therefore, the flow of the combustion gas A1 is likely to be separated on the downstream side of the first top portion 2A.

The first cooling hole 8 and the second cooling hole 9 are provided in the liner main body 1 in a staggered manner in a plan view. Further, the first cooling hole 8 and the second cooling hole 9 are arranged in the vicinity of the first valley portion 3A so as to straddle the first valley portion 3A.

The first cooling hole 8 is provided in the first slope portion 4. The position of the first cooling hole 8 in the first direction D1 can be indicated by utilizing the first top 2A. For example, the ratio (S6 / S1) of the wavelength L (distance S1) along the first direction D1 to the distance S6 from the first top 2A along the first direction D1 to the first cooling hole 8. Is 0.08 or more and 0.25 or less, and 0.22 as an example. The axis AX1 of the first cooling hole 8 is substantially orthogonal to the surface of the first slope portion 4. Therefore, the compressed air A2 ejected from the first cooling hole 8 has a velocity component X1 in the same direction as the flow direction (first direction) of the combustion gas A1.

Further, the position of the first cooling hole 8 may be indicated by using the amplitude 2r (distance T1) of the liner main body 100. For example, the ratio of the amplitude 2r from the first top 2A to the second valley 3B to the distance T4 from the first top 2A to the first cooling hole 8 along the third direction D3 (T4 / T1) is 0.10 or more and 0.84 or less, and is 0.63 as an example.

The second cooling hole 9 is provided in the second slope portion 5. Since the second slope portion 5 is on the downstream side of the first slope portion 4 provided with the first cooling hole 8, the second cooling hole 9 is also on the downstream side of the first cooling hole 8. Provided. The position of the second cooling hole 9 can be indicated by using the first top portion 2A as in the case of the first cooling hole 8. For example, the ratio (S7 / S1) of the wavelength L (distance S1) to the distance S7 from the first top 2A to the second cooling hole 9 along the first direction D1 is 0.22 or more and 0.45. It is as follows, and it is 0.28 as an example. The axis AX2 of the second cooling hole 9 is substantially orthogonal to the surface of the second slope portion 5. Therefore, the compressed air A2 ejected from the second cooling hole 9 has a velocity component X2 in the direction opposite to the flow direction of the combustion gas A1.

Further, the position of the second cooling hole 9 may be indicated by using the amplitude 2r (distance T1) of the liner main body 100. For example, the ratio (T5 / T1) of the amplitude 2r (distance T1) to the distance T5 from the first top 2A to the second cooling hole 9 along the third direction D3 is 0.40 or more and 0. It is 84 or less, and is 0.66 as an example. Here, in the third direction D3, the second cooling hole 9 is provided at a position farther from the first top portion 2A than the first cooling hole 8. That is, the second cooling hole 9 is provided below the first cooling hole 8.

Further, the distance S8 between the first cooling hole 8 and the second cooling hole 9 along the first direction D1 is set to be relatively small. That is, the second cooling hole 9 is provided so as to approach the first cooling hole 8 on the upstream side. It should be noted that the second cooling hole 9 is not provided on the first slope portion 4 beyond the first valley portion 3A. For example, the ratio (S8 / S1) of the distance S8 between the first cooling hole 8 and the second cooling hole 9 with respect to the wavelength L (distance S1) of the liner body 1 is 0.02 or more and 0.15 or less. As an example, it is 0.06.

As shown in FIG. 2, the first cooling hole 8 has a first inner diameter F1. A plurality of first cooling holes 8 are formed at the same distance as one wavelength or two wavelengths on the first axis L1 extending in the first direction D1. FIG. 2 shows a configuration in which the first cooling hole 8 is provided for every two wavelengths. Further, a plurality of first cooling holes 8 are formed at a predetermined pitch on the third axis L3 extending in the second direction D2.

The second cooling hole 9 has a second inner diameter F2. The second inner diameter F2 is larger than the first inner diameter F1. For example, the ratio (F1 / F2) of the first inner diameter F1 and the second inner diameter F2 is 0.9. A plurality of second cooling holes 9 are formed at the same distance as one wavelength or two wavelengths on the second axis L2 extending in the first direction D1. FIG. 2 shows a configuration in which a second cooling hole 9 is provided for every two wavelengths. The second axis L2 is parallel to the first axis L1 and is set so as to be separated from the second direction D2. Therefore, in the first direction D1, the first cooling hole 8 and the second cooling hole 9 are not formed on the same axis. That is, the second cooling hole 9 is on the downstream side of the first cooling hole 8 and is formed between the pair of the first cooling holes 8.

Further, a plurality of second cooling holes 9 are formed at a predetermined pitch on the fourth axis L4 extending in the second direction D2. The fourth axis L4 is parallel to the third axis L3. The fourth axis L4 is set on the downstream side with respect to the third axis L3. Therefore, the second cooling hole 9 is provided on the downstream side of the first cooling hole 8.

Due to the arrangement of the first cooling hole 8 and the second cooling hole 9, as described above, the first cooling hole 8 and the second cooling hole 9 are formed in a staggered manner in a plan view. ..

Next, the action and effect of the liner body 1 will be described.

The first cooling hole 8 is provided on the first slope portion 4. The first slope portion 4 is provided between the first top portion 2A and the first valley portion 3A. Further, the first valley portion 3A is provided between the first top portion 2A and the second top portion 2B. Therefore, the second top 2B is provided on the downstream side of the first cooling hole 8. Further, the compressed air A2 ejected from the first cooling hole 8 located on the upstream side of the second top 2B flows along the first direction D1 and is a vortex rotating around the first direction D1. To form. The vortex excites a part of the combustion gas A1 toward the surface of the liner body 1. Here, the flow toward the surface of the liner main body 1 generated in a part of the combustion gas A1 is obstructed by the second top portion 2B protruding toward the first flow path side. Therefore, it becomes difficult for the combustion gas A1 caught in the vortex rotating around the first direction D1 to flow under the vortex between the first top 2A. As a result, the liner main body 1 can be efficiently cooled by the compressed air A2 ejected from the first cooling hole 8. Therefore, the compressed air A2 can be efficiently used for cooling the liner main body 1.

In the liner main body 1, since the first cooling hole 8 is provided on the first slope portion 4, the compressed air A2 ejected from the first cooling hole 8 has the same velocity component X1 as the first direction D1. Has. Therefore, the second slope portion 5 and the second top portion 2B existing on the downstream side of the first cooling hole 8 can be cooled. On the other hand, the second cooling hole 9 is provided on the second slope portion 5. The compressed air A2 ejected from the second cooling hole 9 has a velocity component X2 in the direction opposite to the first direction D1. Therefore, the first slope portion 4 and the first top portion 2A existing on the upstream side of the second cooling hole 9 can be cooled. Therefore, the compressed air A2 can be efficiently used for cooling the liner main body 1.

The liner body 1 extends in the second direction D2, projects toward the second flow path side, and is adjacent to the downstream side of the second top 2B and the second top 2B in the first direction D1. A second valley portion 3B provided between the top portion 2A and the top portion 2A is further included. According to this configuration, a circulating flow by the compressed air A2 can be suitably generated between the surface of the liner main body 1 and the main stream through which the combustion gas A1 flows between the first top portions 2A. Therefore, the compressed air A2 can be used more efficiently for cooling the liner body 1.

Hereinafter, the effect of cooling by the liner body 1 according to the present embodiment will be described while comparing the cooling effect of the liner body 100 according to the comparative example with the result of confirming by numerical calculation.

<Comparative Example 1, Example 1>
In Comparative Example 1 and Example 1, the temperature distribution on the liner bodies 1, 100 was confirmed. This confirmation was obtained by thermo-fluid analysis by numerical calculation. The liner main bodies 1, 100 according to Example 1 and Comparative Example 1 have the following configurations.
[Comparative Example 1]
Ratio of amplitude (2r) to wavelength L (S1) (T1 / S1): 0.15
Position of the first cooling hole 8 (S6 / S1): 0.07
Position of the second cooling hole 9 (S7 / S1): 0.23
Ratio of the inner diameter of the first cooling hole 8 to the inner diameter of the second cooling hole 9 (F1 / F2): 1.0
[Example 1]
Ratio of amplitude r to wavelength L (T1 / S1): 0.29
Position of the first cooling hole 8 (S6 / S1): 0.22
Position of the second cooling hole 9 (S7 / S1): 0.28
Ratio of the inner diameter of the first cooling hole 8 to the inner diameter of the second cooling hole 9 (F1 / F2): 0.9
Position of second top 2B (S2 / S1): 0.49
Depth of second top 2B (T3 / T1): 0.39

The part (a) of FIG. 5 and the part (b) of FIG. 5 are contour diagrams showing the temperature distribution when the liner main bodies 1 and 100 are viewed in a plan view. Part (a) of FIG. 5 shows the result of Comparative Example 1. Part (b) of FIG. 5 shows the result of Example 1. In the part (a) of FIG. 5 and the part (b) of FIG. 5, the region K1 having the darkest hatching indicates a high temperature region having a relatively high temperature. On the other hand, the region K2 with the thinnest hatching indicates a low temperature region where the temperature is relatively low. That is, in the part (a) of FIG. 5 and the part (b) of FIG. 5, the hatching concentration indicates the relative temperature.

First, referring to the part (a) of FIG. 5 showing the result of Comparative Example 1, it was found that the temperature was higher toward the upstream side. Therefore, it was found that it is difficult to obtain a sufficient cooling effect in the upstream region of the liner main body 100 of Comparative Example 1.

On the other hand, referring to the part (b) of FIG. 5 showing the result of the first embodiment, the regions in the vicinity of the first cooling hole 8 and the second cooling hole 9 arranged on the most upstream side are arranged on the downstream side. In addition, the hatching concentration was shown to be substantially the same as that in the vicinity of the first cooling hole 8 and the second cooling hole 9. Therefore, according to the liner main body 1 of Example 1, it was found that the region on the upstream side also has the same cooling effect as the region on the downstream side.

Further, the cooling effect of the liner body 100 of Comparative Example 1 and the liner body 1 of Example 1 was evaluated using another index. The evaluation index is the film cooling efficiency η. The film cooling efficiency η is defined by the following equation (1).

η: Film cooling efficiency T: Combustion gas temperature T1: Liner body wall temperature T2: Compressed air temperature

FIG. 6 is a graph showing the film cooling efficiency along the first direction D1. The horizontal axis of the graph shown in FIG. 6 indicates the distance from the wave surface start position, and the vertical axis indicates the film cooling efficiency. Graph G6a is the film cooling efficiency of the liner main body 1 according to the first embodiment, and graph G6b is the film cooling efficiency of the liner main body 100 according to Comparative Example 1. With reference to the graph G6a, the film cooling efficiency of the liner main body 1 of Example 1 increased sharply immediately after the start of the wave surface and reached about 0.9. Then, it gradually increased or decreased in a range of about 0.8 to 1.0 in the region for four wavelengths. With reference to the graph G6b, the film cooling efficiency of the liner main body 100 of Comparative Example 1 gradually increases as the distance increases, and the film cooling efficiency of about 0.7 at the maximum in the region of four wavelengths. It turned out to be.

That is, the liner main body 100 of Comparative Example 1 gradually increases in film cooling efficiency toward the downstream side, and approaches the value of the film cooling efficiency of the liner main body 1 of Example 1. Conversely, the liner main body 100 of Comparative Example 1 cannot obtain sufficient cooling efficiency in the upstream region. On the other hand, the liner main body 1 of the first embodiment can obtain a high film cooling efficiency from immediately after the wave surface start point to the downstream side. Therefore, according to the liner main body 1 of Example 1, it was found that the same cooling efficiency as that of the downstream side can be obtained even in the region on the upstream side where sufficient cooling efficiency cannot be obtained in Comparative Example 1.

<Comparative Example 2, Example 2>
Next, the three-dimensional temperature distribution on the liner bodies 1, 100 was confirmed. This confirmation was obtained by thermo-fluid analysis by numerical calculation. The liner main body 100 of Comparative Example 2 has the same configuration as the liner main body 100 of Comparative Example 1. The liner main body 1 of the second embodiment has the same configuration as the liner main body 1 of the first embodiment.

FIG. 7 shows the results of Comparative Example 2. In order to show the three-dimensional temperature distribution, for example, as shown in the part (a) of FIG. 5, a plurality of cross sections 5A, 5B, and 5C orthogonal to the second direction D2 are set, and each cross section has a plurality of cross sections. A two-dimensional temperature distribution was confirmed. The two-dimensional temperature distribution corresponding to the cross section 5A is shown in the part (a) of FIG. The two-dimensional temperature distribution corresponding to the cross section 5B is shown in part (b) of FIG. The two-dimensional temperature distribution corresponding to the cross section 5C is shown in part (c) of FIG. FIG. 7 shows the relative temperature distribution according to the shade of hatching, as in the part (a) of FIG.

As shown in the part (a) of FIG. 7, the compressed air A2 ejected from the first cooling hole 108 blows upward to form a cooling flow (see region H1). Around this cooling flow (region H1), a vortex is generated around the first direction D1 (perpendicular to the paper surface). This vortex entrains the combustion gas A1, and a part of the combustion gas A1 flows to the vicinity of the surface of the liner main body 100. The hatched region (region H2) existing on the downstream side of the first cooling hole 8 indicates that a part of the combustion gas A1 is flowing in by the vortex. That is, a part of the main stream entered below the cooling stream (region H1).

The same tendency can be confirmed in the parts (b) and (c) of FIG. 7. For example, referring to the part (b) of FIG. 7, the first cooling flow (region H1) formed by the compressed air A2 ejected from the first cooling hole 108 and the second cooling hole 9 ejected the air. The second cooling flow (region H3) formed by the compressed air A2 was confirmed. Then, between the first cooling flow (region H1) and the liner main body 100, between the first cooling flow (region H1) and the second cooling flow (region H3), the second cooling flow (region H3). ) And the liner body 100, respectively, are formed with high temperature regions, and it was confirmed that the mainstream combustion gas A1 is flowing into these regions (region H3).

Therefore, according to FIG. 7, it was found that the liner main body 100 according to Comparative Example 1 did not have a sufficient cooling effect in the upstream region.

FIG. 8 shows the results of Example 2. In order to show the three-dimensional temperature distribution, for example, as shown in part (b) of FIG. 5, a plurality of cross sections 5D, 5E, 5F orthogonal to the second direction D2 are set, and each cross section has a plurality of cross sections. A two-dimensional temperature distribution was confirmed. The two-dimensional temperature distribution corresponding to the cross section 5D is shown in part (a) of FIG. The two-dimensional temperature distribution corresponding to the cross section 5E is shown in part (b) of FIG. The two-dimensional temperature distribution corresponding to the cross section 5F is shown in part (c) of FIG. FIG. 8 shows the relative temperature distribution according to the shade of hatching, as in the part (b) of FIG.

Part (a) of FIG. 8 shows the temperature distribution of the cross section on the first axis L1. Referring to the part (a) of FIG. 8, the cooling flow (region H7) formed by ejecting from the first cooling hole 8 forms a circulating flow (R8) between the first top 2A. It turned out that there was. Therefore, it was found that the temperature between the first top 2A was shown by relatively thin hatching, which was lower than the temperature of the mainstream combustion gas A1. Therefore, it was confirmed that the surface of the liner body 1 was sufficiently cooled.

Further, the part (b) in FIG. 8 shows the temperature distribution of the cross section on the axis set between the first axis L1 and the second axis L2. As shown in part (b) of FIG. 8, between the first axis L1 and the second axis L2, that is, the first cooling hole 8 and the second cooling hole 9 in the second direction D2. It was also found that the inflow of the mainstream combustion gas A1 was suppressed and the surface of the liner main body 100 was covered with the compressed air A2.

Further, the part (c) of FIG. 8 shows the temperature distribution of the cross section on the second axis L2. Referring to the part (c) of FIG. 8, a cooling flow (region H9) having a velocity component in the direction opposite to the mainstream direction (first direction D1) is ejected from the second cooling hole 9. all right. The compressed air A2 forming the cooling flow cools the combustion gas A1 forming the main stream, and a part of the compressed air A2 is formed on the first slope portion 4 and the first top portion 2A located upstream of the second cooling hole 9. It turned out to flow toward.

Therefore, according to FIG. 8, it was found that the liner main body 1 according to the second embodiment can obtain a sufficient cooling effect even on the upstream side including the first cooling hole 8.

<Comparative Example 3, Example 3>
Next, the effect of the positions of the second cooling holes 9, 109 was confirmed. This confirmation was obtained by numerical fluid analysis. The liner main body 100 of Comparative Example 3 has the same configuration as the liner main body 100 of Comparative Example 1. The liner main body 1 of the third embodiment has the same configuration as the liner main body 1 of the first embodiment.

9 and 10 show a cross-sectional view of the liner bodies 1, 100. FIG. 9 shows the results of Comparative Example 3. FIG. 10 shows the results of Example 3. Then, in FIGS. 9 and 10, the first streamline R1 and the second streamline R2 are shown. The first streamline R1 shows the flow of the compressed air A2 ejected from the first cooling holes 8 and 108. The second streamline R2 shows the flow of the compressed air A2 ejected from the second cooling holes 9, 109.

As shown in FIG. 9, in the liner main body 100 according to Comparative Example 3, both the first streamline R1 and the second streamline R2 are blown upward, and the mainstream combustion gas A1 can enter below the streamline R1. Was confirmed. It was also confirmed that no flow toward the upstream side was formed in the vicinity of each of the first cooling holes 108, particularly with respect to the first cooling hole 108. Therefore, it was found that it is difficult to obtain a sufficient cooling effect on the upstream side of the first cooling hole 108.

On the other hand, as shown in FIG. 10, in the liner main body 1 of Example 3, it was confirmed that a flow forming a circulating flow was generated between the first top 2A (see region H10). Further, the compressed air A2 ejected from the second cooling hole 9 has a velocity component X2 (FIG. 4) toward the upstream side, and has a cooling effect even in a region on the upstream side with respect to the first cooling hole 8. It was found that it was preferably obtained.

The present invention has been described in detail above based on the embodiment. However, the present invention is not limited to the above embodiment. The present invention can be modified in various ways without departing from the gist thereof.

For example, in the above embodiment, the jet engine 10 is exemplified as a combustion device. The combustion device to which the liner body 1 can be applied is not limited to the jet engine 10. For example, examples of the combustion device include a boiler and a gas turbine.

1,100 Liner body 2A 1st top 2B 2nd top 3A 1st valley 3B 2nd valley 4 1st slope 5 2nd slope 6 3rd slope 7 4th slope Part 8,108 First cooling hole 9,109 Second cooling hole 10 Jet engine 11 Fan 12 Compressor 13 Combustor 14 Turbine 15a Inner housing 15b Outer housing 16 Shaft 21 Case 22 Burning unit 23 Opening 31, 32 Gap A Rotating axis A1 Combustion gas A2 Compressed air AX1 Axis line AX2 Axis line D1 First direction D2 Second direction D3 Third direction F1 First inner diameter F2 Second inner diameter G6a Graph G6b Graph L1 First axis L2 Second Axis line L3 Third axis line L4 Fourth axis line r Amphitheater R Slope R1 First streamline R2 Second streamline η Film cooling efficiency

Claims (2)

A liner body that separates a first flow path through which a first gas containing a first temperature flows and a second flow path through which a second gas containing a second temperature lower than the first temperature flows. Prepare,
The liner body
A plurality of gases are provided in the first direction so as to extend in a second direction intersecting the first direction in which the first gas and the second gas flow and project toward the first flow path side. The first top and
A second apex extending in the second direction and provided between the first apex in the first direction so as to project toward the first flow path side.
Extending in the second direction, projecting toward the second flow path side, and the first top and the second top adjacent to the downstream side of the first top in the first direction. The first valley between the two and
A first slope portion formed between the first top portion and the first valley portion adjacent to the downstream side of the first top portion in the first direction,
A first cooling hole provided on the first axis extending in the first direction on the first slope portion and communicating the first flow path and the second flow path, and a first cooling hole.
A second slope portion formed between the first valley portion and the second top portion adjacent to the downstream side of the first valley portion in the first direction,
A second cooling hole provided on the second axis extending in the first direction on the second slope portion and communicating the first flow path and the second flow path is included. Liner for combustion equipment. Extending in the second direction, projecting toward the second flow path side, and the second top and the first top adjacent to the downstream side of the second top in the first direction. The liner for a combustion device according to claim 1, further comprising a second valley portion provided between the two.