JP2008274774A - Gas turbine combustor and gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor properly cooling the gas turbine combustor according to heat load by combustion gas. <P>SOLUTION: The gas turbine combustor comprises: an inlet header provided on a combustion gas downstream side of a wall portion of an inner tube 52 which is provided in a tubular shape so that a flow of the combustion gas is formed inside; a plurality of cooling passages 53 connected to the inlet header and provided in the wall portion in parallel along a flow direction of the combustion gas; and a cooling air outlet portion connected to the cooling passages 53 and provided on an exhaust gas upstream side of the wall portion. The gas turbine combustor is characterized in that the cooling passages 53 are reduced in their flow path cross sectional area toward the flow direction of the cooling air. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a gas turbine combustor having a cooling structure and a gas turbine.

  The gas turbine combustor has a cooling structure because the wall temperature exceeds the durable temperature of the material by the combustion gas flowing inside. As such a cooling structure for a gas turbine combustor, many methods for cooling by flowing a cooling medium through a wall have been proposed (see, for example, Patent Document 1).

Japanese Patent Laid-Open No. 10-37712

  However, the conventional cooling structure of the gas turbine combustor has been considered to flow the cooling medium through the wall, but has not performed appropriate cooling according to the heat load of the wall. For example, the combustion gas flowing in the combustor has a higher combustion load on the downstream side of the combustor because the combustion temperature rises as it flows downstream after ignition. Therefore, in the conventional cooling structure for a gas turbine combustor, a local high temperature portion may occur in the wall portion.

  This invention is made | formed in view of such a situation, Comprising: It is providing the gas turbine combustor and gas turbine which can cool a gas turbine combustor appropriately according to the thermal load by combustion gas. Objective.

In order to solve the above problems, the gas turbine combustor and the gas turbine of the present invention employ the following means.
That is, a gas turbine combustor according to the present invention includes a cooling medium inlet portion provided on the downstream side of the combustion gas in a wall portion formed in a cylindrical shape so that a flow of combustion gas is formed therein, and the cooling medium. A plurality of cooling medium passages connected to the inlet and provided in parallel in the flow direction of the combustion gas in the wall, and connected to the cooling medium passage and provided on the combustion gas upstream side of the wall In the gas turbine combustor including the cooling medium outlet, the cooling medium passage has a flow path cross-sectional area that decreases in the flow direction of the cooling medium.

The cooling medium flows from the cooling medium inlet on the downstream side of the combustion gas toward the cooling medium outlet on the upstream side of the combustion gas. That is, the cooling medium flows in the cooling medium passage in the direction opposite to the flow of the combustion gas. Therefore, the low temperature cooling medium before the heat exchange with the combustion gas can be led to the downstream side of the combustion gas where the heat load due to the combustion gas is large.
Further, since the flow path cross-sectional area of the cooling medium passage is decreased in the flow direction of the cooling medium, the flow velocity of the refrigerant flowing in the cooling medium passage increases toward the downstream side. As the cooling medium flows downstream, the temperature rises due to heat exchange with the combustion gas, so the temperature difference with the combustion gas decreases and cooling efficiency decreases.However, increasing the flow rate of the cooling medium reduces the heat transfer coefficient. By increasing it, it was decided to make up for the shortcomings caused by the increase in the coolant temperature. Thereby, the partial temperature rise of the wall part of a gas turbine combustor can be suppressed over the flow direction of combustion gas.
Examples of the cooling medium include air after extracting a part of compressed air from the gas turbine compressor and increasing the pressure, steam from an exhaust heat recovery boiler, and the like.

  Furthermore, in the gas turbine combustor according to the present invention, the flow path cross-sectional shape of the coolant passage decreases in the thickness direction of the wall portion in the flow direction of the coolant.

  Since the cross-sectional shape of the flow path is set so as to reduce the dimension of the wall in the thickness direction toward the flow direction of the cooling medium, the flow path breaks without changing the pitch of the adjacent cooling medium paths over the flow direction of the cooling medium. The area can be reduced. On the other hand, when changing the dimension in the direction in which the cooling medium passages are adjacent to each other, it is necessary to change the pitch between the passages in the cooling medium flow direction. Becomes difficult. Therefore, according to the present invention, the cooling medium passages can be densely arranged by reducing the pitch of the cooling medium passages, so that the cooling performance can be improved.

  Furthermore, in the gas turbine combustor according to the present invention, the cooling medium passages have substantially the same flow passage cross-sectional areas, and are smaller on the downstream side of the cooling medium than on the upstream side of the cooling medium. It is characterized by its number.

By using a smaller number of cooling medium passages on the downstream side of the cooling medium than on the upstream side of the cooling medium, the total flow passage cross-sectional area is reduced on the downstream side, and the flow rate of the cooling medium on the downstream side is increased. The heat transfer rate can be increased.
Further, the cooling capacity can be partially changed largely by changing the number of the cooling medium passages. Therefore, even if the heat load of the combustor changes partly, it is possible to respond flexibly.

  The gas turbine of the present invention includes any one of the gas turbine combustors described above, a compressor that supplies compressed air to the combustor, and a turbine that is rotated by the combustion gas from the combustor. It is characterized by that.

  By providing the gas turbine combustor described above, the combustion temperature can be increased and the turbine inlet temperature can be increased. Thereby, a highly efficient gas turbine can be provided.

  The gas turbine according to the present invention further includes a boosting unit that pressurizes a part of the compressed air compressed by the compressor. The compressed air boosted by the boosting unit is used as a cooling medium for the gas turbine combustor. A cooling medium after cooling the turbine combustor is used as combustion air.

  Since the combustor is cooled after increasing the pressure of a part of the compressed air compressed by the compressor, the pressure loss generated when the combustor is cooled can be suppressed to a minimum, and the combustor can be appropriately cooled. Moreover, since the air which cooled the combustor is used as combustion air together with the compressed air compressed by the compressor, the combustion air does not decrease, and an increase in NOx emissions due to an increase in combustion temperature can be suppressed. .

  Since the flow path cross-sectional area of the cooling medium passage decreases in the flow direction of the cooling medium, the gas turbine combustor can be appropriately cooled according to the heat load caused by the combustion gas.

[First Embodiment]
Hereinafter, a first embodiment of the present invention will be described with reference to the drawings.
FIG. 1 shows a schematic diagram of a gas turbine according to the present embodiment. FIG. 2 shows a schematic configuration of the gas turbine. As shown in these drawings, the gas turbine includes a compressor 11, a combustor 12, and a turbine 13, and a generator 14 is connected to the turbine 13. The compressor 11 has an air intake port 15 for taking in air, a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16, and an extraction manifold 19 is provided on the outside thereof. Yes. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner. In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately provided in a turbine casing 20.

An exhaust chamber 23 is continuously provided in the turbine casing 20 of the turbine 13, and the exhaust chamber 23 has an exhaust diffuser 24 that is continuous with the turbine 13.
Further, the rotor 25 is positioned so as to pass through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 23, and the end portion on the compressor 11 side is rotatably supported by the bearing portion 26. On the other hand, an end portion on the exhaust chamber 23 side is rotatably supported by a bearing portion 27.
A plurality of disk plates are fixed to the rotor 25, the rotor blades 18 and 22 are connected, and the drive shaft of the generator 14 is connected to the end on the exhaust chamber 23 side.

  With the above configuration, the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature and high-pressure compressed air. The fuel is burned by supplying a predetermined fuel to the compressed air. The high-temperature and high-pressure combustion gas generated in the combustor 12 drives and rotates the rotor 25 by passing through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13, and is connected to the rotor 25. While generating power by applying rotational power to the generator 14, the exhaust gas is converted into static pressure by the exhaust diffuser 24 in the exhaust chamber 23 and then released to the atmosphere.

In the combustor 12, as shown in FIG. 3, a combustor inner cylinder 32 is supported by a combustor outer cylinder 31, and a combustor tail cylinder 33 is connected to a tip portion of the combustor inner cylinder 32 so that a combustor casing is formed. It is configured.
A flow of combustion gas is formed in a space surrounded by the combustor inner cylinder 32.
A pilot nozzle 34 is provided in the center of the combustor inner cylinder 32, and a plurality of premixing nozzles 35 are provided on the inner peripheral surface of the combustor inner cylinder 32 along the circumferential direction. Is provided. A pilot cone 36 is attached to the tip of the pilot nozzle 34.

  Therefore, when high-temperature and high-pressure compressed air flows from the compressor casing 16 in the compressor 11 into the combustor 12, the compressed air is mixed with the fuel injected from the main fuel rods in each premixing nozzle 35. The swirl flow of the premixed gas flows into the combustor inner cylinder 32. On the other hand, in the pilot nozzle 34, the compressed air is mixed with the fuel injected from the pilot fuel rods, and this air-fuel mixture is ignited and burned by a not-shown type fire and becomes combustion gas in the combustor inner cylinder 32. Erupts. A part of the combustion gas flows into the combustor inner cylinder 32 and the combustor tail cylinder 33 from each premixing nozzle 35 by being ejected so as to diffuse into the combustor inner cylinder 32 with a flame. It is ignited by the premixed gas and burns.

  In the gas turbine configured as described above, as shown in FIG. 1, a pressure increasing device (for example, a compressor or a blower) 41 that extracts and pressurizes a part of the compressed air compressed by the compressor 11 from the passenger compartment, A combustor cooling structure 42 that cools the combustor 12 with compressed air boosted by the booster 41 is provided, and compressed air after cooling the combustor 12 is supplied to the combustor 12.

  That is, the compressed air supply line 43 connected from the compressor 11 to the combustor 12 is branched in the middle to form a compressed air branch line 44, and is connected to the booster 41. The combustor cooling structure 42 is a large number of cooling passages (cooling medium passages) formed in the wall portion of the inner cylinder constituting the combustor 12. The booster 41 is connected to the combustor cooling structure 42 by a cooling air supply line 45. The combustor cooling structure 42 is connected by a compressed air supply line 43 and a compressed air circulation line 46, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 through the compressed air supply line 43. . In this case, the compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 to be supplied to the compartment of the combustor 12.

  Further, a fuel supply line 47 that supplies fuel to the combustor 12 is connected to the combustor 12. Further, the combustor 12 is connected to the turbine 13 by a combustion gas discharge line 48.

Therefore, in the compressor 11, the taken-in air passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature / high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43, that is, compressed air extracted from the passenger compartment is branched into the compressed air branch line 44 and supplied to the booster 41, where the pressure is further increased. The compressed air boosted by the booster 41 is supplied to the combustor cooling structure 42 through the cooling air supply line 45 and is cooled by flowing in the wall of the inner cylinder constituting the combustor 12.
The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43. Thus, since the compressed air after cooling can be secured as combustion air, NOx can be reduced by suppressing the flame temperature.

  In the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying a predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

FIG. 4 schematically shows a combustor cooling structure 42 provided in the combustor 12.
The combustor cooling structure 42 includes a large number of cooling passages (cooling medium passages) 53 formed in the wall portion of the inner cylinder 52 constituting the combustor 12. The respective cooling passages 53 are independent and are provided in parallel with each other along the combustion gas flow direction.

  An inlet header (cooling medium inlet portion) 54 is connected to each cooling passage 53. The inlet header 54 is fixed to the outer periphery of the downstream end of the inner cylinder 52 in the combustion gas flow direction. The inlet header 54 has a hollow ring shape so that cooling air flows therethrough. A cooling air supply line 45 is connected to the inlet header 54 (see FIG. 1), and compressed air that has been pressurized by the booster 41 is supplied.

  A cooling air outlet (cooling medium outlet) 55 is connected to an upstream end of each cooling passage 53 in the combustion gas flow direction. The cooling air outlet 55 is configured by an opening (not shown) communicating with each cooling passage 53. The cooling air flowing out from the cooling air outlet 55 is guided to the vehicle compartment 56. Thus, by ensuring the cooling air after cooling to the vehicle compartment 56 as the combustion air, the flame temperature can be suppressed and NOx can be reduced.

FIG. 5 shows the shape of the cooling passage 53 formed in the wall portion of the inner cylinder 52.
FIG. 5A shows a part of the longitudinal section of the wall portion of the inner cylinder 52. In the figure, the cooling air flowing in the cooling passage 53 flows from right to left, that is, in a direction opposite to the combustion gas flow direction.
The cooling passage 53 has a shape in which the dimension (height dimension) H in the thickness direction of the wall portion gradually decreases toward the flow direction of the cooling air. That is, as can be seen by referring to FIG. 5 (c) showing the CC cross section on the upstream side of the cooling air and FIG. 5 (b) showing the BB cross section on the downstream side of the cooling air. The height dimension H1 of the cooling passage 53 is larger on the upstream side of the air, and the height dimension H2 of the cooling passage is smaller on the downstream side of the cooling air. However, the width dimension of the cooling passage 53 (the dimension in the direction in which the cooling passages 53 are adjacent) W is constant at each position in the cooling air flow direction. Further, the pitch P between the adjacent cooling passages 53 does not change at each position in the flow direction of the cooling air and is constant.
Thus, the flow passage area of the cooling passage 53 is formed so as to gradually decrease in the flow direction of the cooling air.

  As shown in FIGS. 5 (b), 5 (c), and 6 (a), the cross-sectional shape of the cooling passage 53 has a bottom on the combustion gas side, and the top has an arc shape. It may be a shape, or may be a circle as shown in FIG. In the case of a circular cross section as shown in FIG. 6 (b), when increasing the height dimension while keeping the pitch constant on the upstream side of the cooling air, a vertically long ellipse extending in the thickness direction. It becomes a shape.

According to the combustor cooling structure 42 having the above-described configuration, the following operational effects can be obtained.
Since the cooling air flows in the cooling passage 53 in the direction opposite to the flow of the combustion gas, the low-temperature cooling air before heat exchange with the combustion gas is led to the downstream side of the combustion gas where the heat load due to the combustion gas is large. be able to.
Further, since the flow passage cross-sectional area of the cooling passage 53 is gradually decreased in the flow direction of the cooling air, the flow velocity of the cooling air flowing in the cooling passage 53 increases toward the downstream side. As the cooling air flows downstream, the temperature rises due to heat exchange with the combustion gas, so the temperature difference with the combustion gas decreases and cooling efficiency decreases.However, increasing the flow rate of the cooling air reduces the heat transfer coefficient. By increasing it, it was decided to make up for the drawbacks caused by the rise in cooling air temperature. Thereby, the partial temperature rise of the wall part of the inner cylinder 52 of the combustor 12 can be suppressed over the flow direction of the combustion gas.
Further, since the cross-sectional shape of the flow path is set so that the dimension in the thickness direction of the wall portion decreases in the cooling air flow direction, the pitch P of the adjacent cooling passages 53 is not changed over the cooling air flow direction. The channel cross-sectional area can be reduced. On the other hand, when the dimensions in the direction in which the cooling passages are adjacent to each other are changed, it is necessary to change the pitch between the passages in the cooling air flow direction, so that it is difficult to arrange the cooling passages closely at a small pitch. become. Therefore, according to the present embodiment, the pitch P of the cooling passages 53 can be reduced and the cooling passages 53 can be arranged densely, so that the cooling performance can be improved.

FIG. 7 shows the above effect qualitatively. The horizontal axis of the figure shows the position, the left end means the combustor inlet and the right end means the combustor outlet. Therefore, the combustion gas flows from left to right, and the cooling air flows from right to left. The vertical axis in the figure indicates the size of each parameter.
Curve A shows the heat load due to the combustion gas, and the combustion temperature of the combustion gas ignited at the combustor inlet increases as the combustion reaction proceeds. Therefore, the heat load increases toward the combustor outlet side that is downstream. It is shown.
Curve B shows the temperature of the cooling air, and since it is supplied from the combustor outlet side, the temperature is the lowest on the combustor outlet side, and as the cooling air flows toward the combustor inlet side, heat exchange with the combustion gas occurs. It has been shown that the temperature increases.
A curve C indicates the heat transfer coefficient between the cooling air and the flow path wall, and increases from the combustor outlet side toward the combustor inlet. As described above, since the flow velocity of the cooling air is gradually increased, the heat transfer coefficient increases toward the downstream side of the cooling air, that is, the combustor inlet side.
Therefore, as shown by the curve D, the metal temperature of the inner cylinder 52 of the combustor 12 is sufficiently cooled and maintained at a low temperature because the temperature of the cooling air is low even at the combustor outlet side where the heat load is large. In addition, even if the temperature of the cooling air rises on the inlet side of the combustor and the temperature difference from the combustion gas becomes small, the heat transfer coefficient is increased, so that the temperature is maintained within the allowable temperature.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIG.
Since this embodiment is different from the first embodiment in the configuration of the cooling passage formed in the inner cylinder 52 of the combustor 12 and the other portions are the same, the configuration of the cooling passage will be described below.
As shown in FIG. 8A, the number of cooling passages 53 is smaller on the downstream side of the cooling air than on the upstream side of the cooling air. Note that the cross-sectional areas of the cooling passages 53 are substantially the same.
In other words, the passage intervals (pitch) are arranged relatively densely in the upstream cooling passage 53a, and the passage intervals (pitch) are arranged relatively sparsely in the downstream cooling passage 53b. Then, the upstream side cooling passage 53 a and the downstream side cooling passage 53 b are connected by the merge header 60. Therefore, the cooling air that has flowed through the upstream cooling passage 53 a joins at the joining header 60 and then flows into the downstream cooling passage 53.
As described above, in this embodiment, the number of cooling passages is increased on the upstream side to increase the total flow passage cross-sectional area, and the number of cooling passages is reduced on the downstream side to reduce the total flow passage cross-sectional area. As the cooling air flows from the upstream side to the downstream side, the flow velocity is increased. As a result, an increase in the heat transfer coefficient on the downstream side of the cooling air is realized.
Further, in the present embodiment, since the number of the cooling passages 53 is changed, the cooling capacity can be partially changed greatly. Therefore, even if the heat load of the combustor 12 changes greatly in part, it can be flexibly handled.

[Third Embodiment]
Next, a third embodiment of the present invention will be described with reference to FIGS.
This embodiment is different from the first embodiment in the cooling air flow-out method after cooling the inside of the combustor, and the other points are the same, so the description of common parts is omitted. In addition, this embodiment can use the combustor cooling structure of 1st Embodiment and 2nd Embodiment.

In the present embodiment, the cooled cooling air is caused to flow in the acoustic liner 70 that suppresses the combustion vibration generated in the combustor 12.
The acoustic liner 70 is fixed to the outer periphery of the inner cylinder 52 and upstream of the combustion gas flow. As shown in FIGS. 10A and 10B, the acoustic liner 70 is provided with a large number of communication holes 71 so as to communicate with the combustion gas flow path, and vibrations guided from these communication holes 71 are acoustic liners. Attenuate within 70.
In this embodiment, as shown in FIGS. 10A and 10C, the downstream side of the cooling passage 53 and the inside of the acoustic liner 70 are communicated with each other by forming the introduction hole 73. Thus, the cooling air after passing through the cooling passage 53 flows into the acoustic liner 70 through the introduction hole 73 (see FIG. 10C), and then from the acoustic liner 70 into the combustion gas flow path. (See FIG. 10B).

As described above, in the present embodiment, since the cooled cooling air is allowed to flow out from the acoustic liner 70 to the combustion gas flow path, the combustion gas can be prevented from flowing back into the acoustic liner 70. . Therefore, it is not necessary to separately use purge air in order to prevent the backflow of the combustion gas to the acoustic liner 70.
Moreover, since the cooling air after cooling becomes high temperature by heat exchange with combustion gas, the volume flow volume is increasing. Therefore, the purge capability is higher than that when separate purge air is used. Further, even when the purge air is used together, the purge air amount can be reduced.
Further, since the cooled cooling air is introduced into the combustion gas flow path and used as combustion air, the flame temperature can be suppressed and NOx can be reduced as in the first embodiment.

[Fourth Embodiment]
Next, a fourth embodiment of the present invention will be described with reference to FIG.
This embodiment is different from the first embodiment and the third embodiment in the cooling air flow-out method after cooling the inside of the combustor, and the other points are the same, so the description of common parts is omitted. In addition, this embodiment can use the combustor cooling structure of 1st Embodiment and 2nd Embodiment.
In the present embodiment, a cooling air outlet part (cooling medium outlet part) 57 is provided on the inlet side of the combustor 12 and is formed so that the cooling air flows out toward the combustion gas flow path side. Furthermore, the cooling air outlet 57 is configured by a film cooling hole formed so that the outflowed air flows in a film shape along the inner wall of the inner cylinder 52.

  As described above, according to the cooling air outlet 57 of the present embodiment, the cooling air can be supplied so as to flow in a film shape along the inner wall of the inner cylinder 52. Further, the cooling performance of the combustor 12 can be improved. Moreover, compared with the case where film cooling is performed using air in the passenger compartment, the cooling air after cooling has an increased volume flow rate due to temperature rise, so that the film flow rate can be increased. Thereby, the ability to blow off the flame that flashes back along the wall surface can be increased, and the structural reliability of the combustor 12 can be increased.

  In each of the above embodiments, the compressed air extracted from the compressor is used as the cooling medium supplied to the cooling passage. However, the present invention is not limited to this, and for example, extracted from the exhaust heat recovery boiler. Steam may be used.

It is a mimetic diagram showing a gas turbine concerning one embodiment of the present invention. It is a partial section side view showing a schematic structure of a gas turbine concerning one embodiment of the present invention. It is the partial cross section side view which showed schematic structure of the combustor of the gas turbine of FIG. It is the longitudinal cross-sectional view which showed the outline of the cooling structure of the gas turbine combustor which concerns on one Embodiment of this invention. The combustor cooling structure concerning 1st Embodiment of this invention is shown, (a) is the fragmentary longitudinal cross-section of an inner cylinder wall part, (b) is the fragmentary cross-sectional view in the BB cutting line of (a), ( c) is a partial cross-sectional view taken along the line CC of FIG. The cross-sectional shape of a cooling channel | path is shown, (a) is the partial cross-sectional view of the cooling channel | path made into bowl shape, (b) is the partial cross-sectional view of the cooling channel | path made circular. It is the graph which showed the effect of the present invention qualitatively. The combustor cooling structure concerning 2nd Embodiment of this invention is shown, (a) is the perspective view which showed a part of inner cylinder wall part, (b) is the partial cross-sectional view of an inner cylinder wall part. It is the longitudinal cross-sectional view which showed the outline of the combustor provided with the acoustic liner concerning 3rd Embodiment of this invention. 9 shows a configuration around the acoustic liner in FIG. 9, (a) is a transverse sectional view of the acoustic liner, (b) is a longitudinal sectional view taken along the line BB in (a), and (c) is a C- in (a). It is a longitudinal cross-sectional view in the C cutting line. It is the longitudinal cross-sectional view which showed the combustor concerning 4th Embodiment of this invention.

Explanation of symbols

11 Compressor 12 Combustor (Gas Turbine Combustor)
13 Turbine 41 Booster 52 Inner cylinder 53 Cooling passage (cooling medium passage)
54 Inlet header (cooling medium inlet)
55 Cooling air outlet (cooling medium outlet)

Claims (5)

A cooling medium inlet provided on the downstream side of the combustion gas of the wall formed in a cylindrical shape so that a flow of the combustion gas is formed therein;
A plurality of cooling medium passages connected to the cooling medium inlet and provided in parallel in the flow direction of the combustion gas in the wall;
A cooling medium outlet connected to the cooling medium passage and provided on the upstream side of the combustion gas of the wall;
In a gas turbine combustor with
The gas turbine combustor, wherein the cooling medium passage has a flow passage cross-sectional area that decreases in a flow direction of the cooling medium.   2. The gas turbine combustor according to claim 1, wherein the flow path cross-sectional shape of the cooling medium passage decreases in the thickness direction of the wall portion in the flow direction of the cooling medium.   The cooling medium passages have substantially the same flow path cross-sectional area, and the number of cooling medium passages on the downstream side of the cooling medium is smaller than that on the upstream side of the cooling medium. Item 5. A gas turbine combustor according to Item 1. A gas turbine combustor according to any one of claims 1 to 3,
A compressor for supplying compressed air to the combustor;
A turbine rotated by combustion gas from the combustor;
A gas turbine comprising: A pressure increasing means for increasing the pressure of a part of the compressed air compressed by the compressor;
Using the compressed air boosted by the boosting means as a cooling medium for the gas turbine combustor,
The gas turbine according to claim 4, wherein the cooling medium after cooling the gas turbine combustor is used as combustion air.

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