JP2018054210A - Liner for combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a liner of a combustor capable of efficiently utilizing low-temperature gas for cooling.SOLUTION: A liner body 1 includes: a plurality of crests 2 in a first direction D1; a plurality of troughs 3 formed at positions different from those of the crests 2 in the first direction D1; a first slope 4 formed between the crest 2 and the trough 3 adjacent to a downstream side; a second slope 6 formed between the trough 3 and the crest 2 adjacent to the downstream side; a first cooling hole 7 provided on the first slope 4; and a second cooling hole 8 provided on the second slope 6. A first length from the crest 2 to the trough 3 adjacent to the downstream side is shorter than a second length from the trough to the crest 2 adjacent to the downstream side.SELECTED DRAWING: Figure 2

Description

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

  A gas turbine as a combustion apparatus includes a combustor. In the combustor, fuel is burned to generate hot gas. Therefore, in order to protect the components disposed around the combustor from the hot gas, a wave-shaped liner as a heat shield is used. For example, Patent Document 1 discloses a liner for a combustor used for a gas turbine.

JP-A-8-278029

  The liner main body disclosed in Patent Document 1 has a cooling hole. The cooling hole takes in air from the outside. The taken-in air as the cold gas is deflected by the inner ring in a direction corresponding to the flow direction of the combustion gas, and flows along the inner surface of the liner body.

  In recent years, from the viewpoint of improving the performance of the combustor, the temperature of the hot gas generated in the combustor tends to increase. On the other hand, the amount of cold gas available for liner cooling is limited. Therefore, a technique capable of efficiently using low temperature gas for cooling the liner is desired.

  The liner for a combustion apparatus according to an aspect of the present invention includes a first flow path through which a first gas including a first temperature flows, and a second gas including a second temperature lower than the first temperature. A liner body is provided to separate the second flow path. The liner body extends in a second direction intersecting the first direction in which the first gas and the second gas flow, and a plurality of liner bodies are provided in the first direction so as to protrude toward the first flow path. A top portion, a plurality of trough portions that extend in the second direction, protrude toward the second flow path, and are formed at positions different from the top portion in the first direction; and the first direction Between the first slope portion formed between the top portion and the valley portion adjacent to the downstream side with respect to the top portion, and the top portion adjacent to the downstream side with respect to the valley portion and the valley portion in the first direction. A second slope portion formed on the first slope portion and a first axis that extends in the first direction at the first slope portion, and communicates the first flow path and the second flow path. The cooling hole is provided on a second axis extending in the first direction at the second slope portion, and connects the first flow path and the second flow path. The first length from the top to the trough adjacent downstream with respect to the top is a first length from the trough to the top adjacent downstream with respect to the trough. Shorter than 2.

  In this liner for a combustion apparatus, since the first cooling hole is provided in the first inclined surface portion, the second gas ejected from the first cooling hole has the same velocity component as that in the first direction. . Therefore, the second slope portion and the top portion existing on the downstream side of the first cooling hole can be cooled. On the other hand, the 2nd cooling hole is provided in the 2nd slope part. The second gas ejected from the second cooling hole has a velocity component in the opposite direction to the first direction. Therefore, the first slope portion and the top portion existing on the upstream side of the second cooling hole can be cooled. Furthermore, the first length from the top to the valley adjacent to the downstream side is shorter than the second length from the valley to the top adjacent to the downstream side. As a result, the second cooling hole can be disposed at a position close to the top on the upstream side, so that the second gas is directed from the second cooling hole toward the first slope portion and the top on the upstream side. Can be efficiently ejected. Therefore, the second gas can be efficiently used for cooling the liner body.

  The first axis and the second axis may be alternately set in the second direction. According to the arrangement of the first axis and the second axis, the first cooling hole and the second cooling hole are not arranged on the same axis in the first direction. Therefore, when the liner body is viewed in plan, the first cooling holes and the second cooling holes are arranged in a staggered manner. According to this arrangement, it is possible to close the interval between the holes from which the second gas is ejected in the second direction. Therefore, the cooling effect by the second gas in the second direction can be made uniform, and the temperature distribution in the second direction can be made more uniform.

  The shape of the liner main body is a wave shape in which top portions and trough portions are alternately provided along the first direction, and the first cooling hole is provided at the most upstream side at least in the plurality of first slope portions. The second cooling hole may be provided at least on the second slope portion provided on the most upstream side of the plurality of second slope portions. According to this structure, the top part arrange | positioned at the most upstream side of a liner main body can be cooled efficiently.

  ADVANTAGE OF THE INVENTION According to this invention, the liner for combustion apparatuses which can utilize low temperature gas efficiently for cooling of a liner is provided.

FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine provided with a combustion apparatus liner according to the present embodiment. FIG. 2 is an enlarged perspective view showing a part of the liner body. FIG. 3 is a cross-sectional view of a part of the liner body. FIG. 4 is a diagram for defining the waveform shape of the liner body. FIG. 5 is a diagram for defining the waveform shape of the liner body according to the comparative example. FIG. 6 is a contour diagram showing the temperature distribution on the surface of the liner body shown in FIG. FIG. 7 is a contour diagram illustrating the temperature distribution on the surface of the liner body according to the first embodiment. FIG. 8 is a contour diagram showing a temperature distribution when a part of FIG. 7 is viewed in cross section. FIG. 9 is a graph showing the film cooling efficiency along the first direction.

  DESCRIPTION OF EMBODIMENTS 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 denoted by the same reference numerals, and redundant description is omitted.

  FIG. 1 is a schematic cross-sectional view showing a schematic configuration of a jet engine 10 provided with a combustion apparatus liner (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 outside air into the jet engine 10, and is provided around the rotation axis A of the shaft portion 16 that is rotationally driven. 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 part of the velocity energy of the combustion gas A1 (first gas) generated by the combustion of 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 15 a and the shaft portion 16. An outer housing 15b is provided on the outer peripheral side of the fan 11 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 the stationary blade 11b.

  In the jet engine 10 having such a configuration, air is taken into the jet engine 10 by the fan 11. A part of the air flows between the inner housing 15 a and the shaft portion 16 and is supplied to the compressor 12. Further, another 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 combusted with fuel in the combustor 13. A part of the velocity energy of the combustion gas A <b> 1 generated by the 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 A1 is used to give propulsion to the jet engine 10 when the combustion gas A1 is exhausted from the rear part of the jet engine 10. As a result, the jet engine 10 is propelled. In the present specification, the terms “upstream” and “downstream” are used based on the flow of air taken into the jet engine 10. Further, the terms “outer peripheral side” and “inner peripheral 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 so as to surround the shaft portion 16 in the housing 15. A gap 31 is provided between the case 21 and the housing 15. A gap 32 is also provided between the case 21 and the shaft portion 16. These gaps 31 and 32 correspond to the 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 body 1 separates the first flow path through which the combustion gas A1 flows and the second flow path through which the compressed air A2 flows. Therefore, the liner main 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 A <b> 1 is released 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. And combustion gas A1 is formed when an ignition device ignites mixture. The combustion gas A <b> 1 flows through the case 21 and is provided to the turbine 14 from 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 A <b> 2 provided from the compressor 12 flows in the gap 31 between the case 21 and the housing 15 and the gap 32 between the case 21 and the shaft portion 16. The compressed air A2 flowing through the gaps 31 and 32 has a temperature 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 A <b> 2 is taken into the case 21 by providing a plurality of cooling holes in the liner body 1 of the case 21. The compressed air A2 forms a temperature boundary layer described later between the high-temperature combustion gas A1 and the liner body 1. This temperature boundary layer prevents the inner surface of the liner body 1 from being directly exposed 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 body 1. FIG. 3 is a cross-sectional view of a part of the liner body 1. As shown in FIGS. 2 and 3, the liner body 1 is a thin plate having a corrugated cross section. The liner body 1 is made of a plate material such as a nickel-base heat-resistant alloy. The liner body 1 has a top portion 2, a valley portion 3, a first slope portion 4, a second slope portion 6, a first cooling hole 7, and a second cooling hole 8.

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

  The valley portion 3 is a portion protruding toward the outside of the case 21. That is, the trough 3 protrudes toward the second flow path through which the compressed air A2 flows. Similar to the top 2, the valley 3 extends in the second direction D2. The valley 3 is repeatedly provided with a predetermined pitch along the first direction D1.

  The first slope portion 4 is formed between the top portion 2 and the valley portion 3 in the first direction D1. Accordingly, the first slope portion 4 has a substantially constant negative slope (down slope) in the first direction D1. On the other hand, the second slope 6 is formed between the valley 3 and the top 2 in the first direction D1. Therefore, the second slope 6 has a substantially constant positive slope (uphill slope) in the first direction D1.

  That is, the liner body 1 has a top portion 2, a first slope portion 4, a trough portion 3, and a second slope portion 6 formed in this order along the first direction D1 (from upstream to downstream). Yes. And the structure containing these top parts 2, the 1st slope part 4, the trough part 3, and the 2nd slope part 6 is repeatedly provided along the 1st direction D1. Accordingly, when the liner body 1 is viewed in cross section, the liner body 1 has a so-called wave shape.

  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 body 1. As shown in FIG. 4, the distance from the top 2 to the next top 2 is defined as a wavelength L. The distance from the top 2 to the adjacent valley 3 is defined as the valley bottom position m. The distance from the top 2 to the valley 3 is defined as the amplitude (2r). Assuming a center line passing through the center of the distance from the top 2 to the valley 3, the distance from the top 2 to the center line is defined as amplitude (r), and the distance from the valley 3 to the center line is defined as the amplitude (r ). The liner body 1 has a relatively large amplitude. Specifically, “relatively large amplitude” can be defined as a ratio of amplitude (r) to wavelength L (amplitude r / wavelength L is 0.08 or more and 0.25 or less. The ratio of amplitude (r) to wavelength L (amplitude r / wavelength L) is 0.152.

  Further, the first length S1 from the top 2 to the valley 3 adjacent to the downstream side with respect to the top 2 is the second length S1 from the valley 3 to the top 2 adjacent to the valley 3 with respect to the downstream side. Shorter than length S4. According to such a configuration, the valley portion 3 is closer to the upstream top portion 2 than the downstream top portion 2. “The valley 3 is closer to the upstream top 2 than the downstream top 2” can also be indicated by the valley bottom position m and the wavelength L. For example, the ratio of the valley position m to the wavelength L (valley position m / wavelength L) is 0.20 or more and 0.40 or less, and is 0.265 as an example. Further, according to such a configuration, the third length S5 of the first slope portion 4 along the first axis L1 is equal to the fourth length of the second slope portion 6 along the second axis L2. It can be said that it is shorter than the length S6. For this reason, the slope R1 of the first slope portion 4 with respect to the first direction D1 is larger than the slope R2 (that is, the slope) of the second slope portion 6 with respect to the first direction D1. For this reason, the flow of the combustion gas A1 is easily separated at the top portion 2.

  The first cooling holes 7 and the second cooling holes 8 are provided in a staggered manner in the liner body 1 in plan view. The first cooling hole 7 is provided in the first slope portion 4. The position of the first cooling hole 7 in the first direction D1 can be indicated by using the valley bottom position m. For example, the ratio between the distance (S1) from the top 2 to the valley bottom position m along the first direction D1 and the distance (S2) from the top 2 to the first cooling hole 7 along the first direction D1. (S2 / S1) is 0.14 or more and 0.80 or less, and can be 0.692 as an example. The axis AX1 of the first cooling hole 7 is substantially orthogonal to the surface of the first slope portion 4. For this reason, the direction of the axis AX1 has a velocity component X1 in the positive direction in the first direction D1. That is, the compressed air A2 ejected from the first cooling hole 7 has the same direction component as the direction in which the combustion gas A1 flows.

  Further, the second cooling hole 8 is provided in the second inclined surface portion 6. Similarly to the first cooling hole 7, the position of the second cooling hole 8 can be indicated by using the valley position m. For example, the ratio of the distance (S1) from the top 2 to the valley position m along the first direction D1 and the distance (S3) from the top 2 to the second cooling hole 8 along the first direction D1. (S3 / S1) is 1.05 or more and 1.50 or less, and can be 1.206 as an example. The axis AX2 of the second cooling hole 8 is substantially orthogonal to the surface of the second inclined surface portion 6. For this reason, the direction of the axis AX2 has a velocity component X2 in the negative direction in the first direction D1. That is, the compressed air A2 ejected from the second cooling hole 8 has a component opposite to the direction in which the combustion gas A1 flows.

  As shown in FIG. 2, the first cooling hole 7 has a first inner diameter F1. A plurality of first cooling holes 7 are formed with the same distance as one wavelength or two wavelengths in the first axis L1 extending in the first direction D1. FIG. 2 shows a configuration in which the first cooling holes 7 are provided for every two wavelengths. A plurality of the first cooling holes 7 are formed with a predetermined pitch on the third axis L3 extending in the second direction D2.

  The second cooling hole 8 has a second inner diameter F2. The second inner diameter F2 is smaller than the first inner diameter F1. For example, the ratio (F1 / F2) between the first inner diameter F1 and the second inner diameter F2 is 1.65. A plurality of second cooling holes 8 are formed with the same distance as one wavelength or two wavelengths in the second axis L2 extending in the first direction D1. FIG. 2 shows a configuration in which second cooling holes 8 are provided for every two wavelengths. The second axis L2 is set to be parallel to the first axis L1 and separated in the second direction D2. Accordingly, in the first direction D1, the first cooling hole 7 and the second cooling hole 8 are not formed on the same axis. That is, the second cooling hole 8 is formed downstream of the first cooling hole 7 and between the pair of first cooling holes 7.

  A plurality of second cooling holes 8 are formed with 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 8 is provided on the downstream side of the first cooling hole 7. In other words, it can be said that the second cooling hole 8 is provided closer to the valley 3 than the first cooling hole 7. According to the arrangement of the second cooling holes 8 as described above, the flow of the compressed air A2 ejected from the second cooling holes 8 is brought close to the valley portion 3 so as to interfere with the flow of the valley.

  By arranging the first cooling hole 7 and the second cooling hole 8 as described above, as described above, the first cooling hole 7 and the second cooling hole 8 are formed in a staggered pattern in plan view. .

Here, when the shape of the liner main body 1 of the embodiment and the shape of the liner main body according to the comparative example are compared, Table 1 is obtained.

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

  In the liner main body 1 of this liner for a combustion apparatus, since the first cooling hole 7 is provided in the first slope portion 4, the compressed air A2 ejected from the first cooling hole 7 is in the first direction. It has the same velocity component X1 as D1. Accordingly, the second slope portion 6 and the top portion 2 existing on the downstream side of the first cooling hole 7 can be cooled. On the other hand, the second cooling hole 8 is provided in the second inclined surface portion 6. The compressed air A2 ejected from the second cooling hole 8 has a velocity component X2 in the reverse direction with respect to the first direction D1. Therefore, the first slope portion 4 and the top portion 2 existing on the upstream side of the second cooling hole 8 can be cooled. Furthermore, the first length S1 from the top 2 to the valley 3 adjacent downstream is shorter than the second length S4 from the valley 3 to the top 2 adjacent downstream. As a result, the second cooling hole 8 can be disposed at a position close to the upstream top portion 2, so that the compressed air A <b> 2 is supplied from the second cooling hole 8 to the first slope portion 4 on the upstream side and It can be efficiently ejected toward the top 2. Therefore, the compressed air A2 can be efficiently used for cooling the liner body 1.

  The first axis L1 and the second axis L2 are alternately set in the second direction D2. According to the arrangement of the first axis L1 and the second axis L2, the first cooling hole 7 and the second cooling hole 8 may be arranged on the same axis in the first direction D1. Absent. Accordingly, when the liner body 1 is viewed in plan, the first cooling holes 7 and the second cooling holes 8 are arranged in a staggered manner. According to this arrangement, it is possible to close the interval between the holes through which the compressed air A2 is ejected in the second direction D2. Therefore, the cooling effect by the compressed air A2 in the second direction D2 can be made uniform, and the temperature distribution in the second direction D2 can be made more uniform.

  The shape of the liner body 1 is a wave shape in which the top portions 2 and the valley portions 3 are alternately provided along the first direction D1, and the first cooling holes 7 include at least a plurality of first slope portions 4. In the first slope portion 4 provided on the most upstream side, and the second cooling hole 8 is at least the second slope portion 6 provided on the most upstream side in the plurality of second slope portions 6. Is provided. According to this structure, the top part 2 arrange | positioned in the most upstream side of the liner main body 1 can be cooled efficiently.

  Hereinafter, the cooling effect of 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>
FIG. 5 is a diagram illustrating a cross-sectional shape of the liner main body 100 according to the first comparative example. The liner body 100 of the comparative example has a wave shape that is a combination of arc shapes. Further, the liner body 100 of the comparative example includes a top portion 102, a valley portion 103, a first cooling hole 107, and a second cooling hole 108. The wavy shape of the liner main body 100 according to the comparative example, the position of the first cooling hole 107, and the position of the second cooling hole 108 are the liner L according to the embodiment using the wavelength L, the amplitude r, and the valley bottom position m described above. Contrast with the main body 1. In the liner body 100 of the comparative example, the ratio (r / L) between the amplitude r and the wavelength L is 0.074 as an example. In the liner body 100 of the comparative example, the ratio (S2 / S1) between the distance (S2) from the top 2 to the first cooling hole 7 and the distance (S1) from the top 2 to the valley position m is, for example, 0.139. In the liner body 100 of the comparative example, the ratio (S3 / S1) of the distance (S3) from the top 2 to the second cooling hole 8 and the distance (S1) from the top 2 to the valley position m is, for example, 0.483. The ratio (r / S1) between the wavelength L and the distance (S1) from the top 2 to the valley position m is 0.500 as an example.

In FIG. 6, the temperature distribution on the surface of the liner body 1 is shown by a contour diagram.
The hatched portion (region K1) is a region where the temperature is relatively high. On the other hand, the hatched portion (region K2) is a region where the temperature is relatively low. That is, the shade density corresponds to the relative temperature level. In the perspective view shown in FIG. 6, the combustion gas A1 and the compressed air A2 flow from the upper left to the lower right. Referring to the contour diagram, it was found that the temperature was higher on the upstream side. In particular, it has been found that the vicinity of the first cooling hole 107 and the second cooling hole 108 arranged on the most upstream side is a region having the highest temperature. Therefore, it has been found that in the liner body 100 of the comparative example, it is difficult to obtain a sufficient cooling effect in a region in the vicinity of the first cooling hole 107 and the second cooling hole 108 arranged on the most upstream side.

<Example 1>
Next, the cooling effect by the liner main body 1 which concerns on an Example was confirmed. The shape of the liner body 1 of the example is as shown in Table 2. In Table 2, the valley bottom position m is a distance from the top 2 on the upstream side to the valley 3 in the first direction D1. The first cooling hole position a is a distance (S2) from the top 2 on the upstream side in the first direction D1 to the axis AX1 of the first cooling hole 7. The second cooling hole position b is a distance (S3) from the top 2 on the upstream side in the second direction D2 to the axis AX2 of the second cooling hole 8.

  FIG. 7 is a contour diagram showing the temperature distribution on the surface of the liner body 1 of the embodiment. As shown in FIG. 7, the first cooling hole 7 and the second cooling hole 8 arranged on the most upstream side are adjacent to the first cooling hole 7 and the second cooling hole arranged on the downstream side. The hatching concentration (region K2) is approximately equivalent to the region near the hole 8. Therefore, it was found that the cooling effect was sufficiently obtained also in the upstream region.

  FIG. 8 is a contour diagram showing an enlarged cross section along the axis L2a in FIG. Referring to FIG. 8, first at the top 2 on the upstream side. It was found that the high temperature region K1 was peeled off from the surface of the liner body 1 (see region K3). This is considered to be due to the fact that the first slope portion 4 continuing to the top portion 2 is greatly inclined with respect to the first direction D1. Next, it was found that the area between the top 2 and the top 2 is indicated by a thin hatched region K4 indicating a relatively low temperature. That is, it was found that the surfaces of the first slope portion 4 and the second slope portion 6 disposed between the top portion 2 and the top portion 2 were sufficiently cooled. This is because the compressed air A2 ejected from the first cooling hole 7 and the compressed air A2 ejected from the second cooling hole 8 interfere with each other, so that the compressed air A2 is between the top 2 and the top 2. It is thought that this is because stagnation tends to occur. Thereby, it becomes difficult for the combustion gas A1 to enter between the top 2 and the top 2, and the temperature rise of the liner body 1 is suppressed. As a result, it has been found that the combustion gas A1 flows above the compressed air A2 having a relatively low temperature that stays between the top 2 and the top 2.

  Furthermore, a part of the compressed air A2 staying between the top part 2 and the top part 2 flows so as to exceed the top part 2 on the downstream side. Therefore, the top 2 on the downstream side is also covered with the compressed air A2 having a relatively low temperature, and it is difficult to directly contact the combustion gas A1 having a relatively high temperature. Accordingly, it has been found that a sufficient cooling effect can be obtained even at the top 2 on the downstream side.

<Comparative example 2, Example 2>
Next, the cooling effect of the liner main body 100 of Comparative Example 2 and the liner main body 1 of Example 2 was evaluated using another index. The shape of the liner body 100 of Comparative Example 2 is the same as the shape of the liner body 100 of Comparative Example 1. Similarly, the shape of the liner body 1 of the second embodiment is the same as the shape of the liner body 1 of the first embodiment. The evaluation index used in Comparative Example 2 and Example 2 is the film cooling effect. The film cooling effect is defined by the following formula (1).

T _h : Combustion gas temperature T _c : Compressed air temperature T (x): Average temperature in the second direction at a distance from the waveform start position

  FIG. 9 is a graph showing the span average film cooling effect along the first direction D1 from the wavefront starting point. The horizontal axis indicates the distance from the wavefront start position, and the vertical axis indicates the film cooling efficiency. Graph G9a is the film cooling efficiency of the liner main body 1 according to Example 2, and graph G9b is the film cooling efficiency η of the liner main body 100 according to Comparative Example 2. As shown in graphs G9a and G9b, the film cooling efficiency η of the liner body 100 of Comparative Example 2 was 0.3 at the maximum in the region for one wavelength. And it turned out that the film cooling efficiency (eta) increases gradually as distance becomes large, and is about 0.5 at the maximum in the area | region for two wavelengths. On the other hand, the film cooling efficiency η of the liner body 1 of Example 2 exceeded 0.5 immediately after the start of the wavefront, and was found to be approximately 0.5 to 0.7 in the region for two wavelengths.

  That is, the liner main body 100 of Comparative Example 2 gradually increases in film cooling efficiency η as it goes downstream, and approaches the film cooling efficiency η of the liner main body 1 of Example 2. In other words, the liner body 1 of the comparative example 2 cannot obtain sufficient cooling efficiency in the upstream region. On the other hand, the liner main body 1 of Example 2 can obtain a substantially constant film cooling efficiency from the wavefront start point to the downstream side. Therefore, according to the liner main body 1 of Example 2, it was found that even in the upstream region where sufficient cooling efficiency cannot be obtained in Comparative Example 2, the cooling efficiency equivalent to that on the downstream side can be obtained.

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

  For example, in the said embodiment, the jet engine 10 was illustrated as a combustion apparatus. The combustion apparatus to which the liner body 1 can be applied is not limited to the jet engine 10. For example, a boiler, a gas turbine, etc. are mentioned as a combustion apparatus.

  Moreover, although the liner main body 1 of the said embodiment provided the 1st cooling hole 7 and the 2nd cooling hole 8 for every wavelength, it is not limited to this structure. The first cooling hole 7 may be provided only at least in the first slope portion 4 provided on the most upstream side in the plurality of first slope portions 4. Further, the second cooling hole 8 may be provided only at least in the second slope portion 6 provided on the most upstream side in the plurality of second slope portions 6. Even if it is this structure, the top part 2 (namely, wavefront start part) provided in the most upstream side can be cooled suitably.

DESCRIPTION OF SYMBOLS 1,100 Liner main body 2,102 Top part 3,103 Valley part 4 1st slope part 6 2nd slope part 7,107 1st cooling hole 8,108 2nd cooling hole 10 Jet engine 11 Fan 12 Compressor 13 Combustor 14 Turbine 15a Inner housing 15b Outer housing 16 Shaft portion 21 Case 22 Combustion unit 23 Opening 31 Clearance 32 Clearance 100 Liner body A Rotating shaft A1 Combustion gas A2 Compressed air a First cooling hole position AX1 Axis AX2 Axis b Two cooling hole positions D1 First direction D2 Second direction F1 First inner diameter F2 Second inner diameter G9a Graph G9b Graph K1, K2, K3, K4 Region L Wavelength L1 First axis L2 Second axis L3 Third axis L4 Fourth axis m Valley position R1, R2 Inclination r, 2r Amplitude S1 First length S4 Second length S5 Third length S6 Fourth Length X1, X2 velocity component η film cooling efficiency

Claims (3)

A liner body separating 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; Prepared,
The liner body is
A plurality of the first gas and the second gas 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. The top,
A plurality of troughs that extend in the second direction, project toward the second flow path side, and are formed at positions different from the top in the first direction;
A first slope portion formed between the top portion and the valley portion adjacent to the downstream side with respect to the top portion in the first direction;
A second slope portion formed between the valley portion and the top portion adjacent to the downstream side with respect to the valley portion in the first direction;
A first cooling hole provided on a first axis extending in the first direction in the first inclined surface portion, and communicating the first flow path and the second flow path;
A second cooling hole provided on a second axis extending in the first direction in the second inclined surface portion, and communicating the first flow path and the second flow path;
The first length from the top to the valley adjacent downstream with respect to the top is shorter than the second length from the valley to the top adjacent downstream with respect to the valley. , Liner for combustion equipment.   The liner for a combustion apparatus according to claim 1, wherein the first axis and the second axis are alternately set in the second direction. The shape of the liner body is a wave shape in which the top and the trough are alternately provided along the first direction,
The first cooling hole is provided at least in the first slope portion provided on the most upstream side in the plurality of first slope portions,
3. The combustion apparatus liner according to claim 1, wherein the second cooling hole is provided at least in the second slope portion provided on the most upstream side in the plurality of second slope portions.