JPH0941991A - Cooling structure of gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To IMPROVEin reliability from the standpoint of operation on a gas turbine combustor by making an excellent cooling effect in this combustor showable with a few cooling media. SOLUTION: This is a cooling structure that cools a combustor liner 3, a transitional duct 6 of a gas turbine and wall surface of other high temperature parts from the outer circumference. It is provided with a porous type plate surrounding the wall surface or the cooled part. A cooling medium flowing along a peripheral surface of this porous type plate is spouted toan inner cricumferential side from holes of this porous plate as a high-speed jet, making it almost vertically collide with the wall surface for impingement cooling. As this porous type plate surrounding the wall surface or the cooled part, it is equipped with a corrugated plate 10 being made up of cylindrical form as a whole, having a lot of grooves 15 along the flowing direction of the cooling medium. Subsequently plural pieces of cooling holes 17 spraying the cooling medium toward the wall surface side or the cooled part is installed in a bottom wall 16 of the groove part 15 projecting toward the inner circumferential side of this corrugated plate 10.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling structure for a gas turbine combustor, and more particularly to a cooling structure for a gas turbine combustor of a type in which walls such as a combustor liner and a transition duct are cooled by a collision jet of a cooling medium. Is.

[0002]

2. Description of the Related Art Conventionally, as a cooling structure for a gas turbine combustor of this type, a porous plate is provided so as to surround the outer surface of the combustor liner at a predetermined distance from the wall surface of the combustor liner, which is the part to be cooled. By arranging them, the driving force due to the pressure difference between the inner and outer circumferences of this porous plate causes air as a cooling medium to form a high-speed jet so that the holes collide almost perpendicularly with the wall of the combustor liner, so-called impingement cooling. It is known to do so.

Here, the air that has flown into the outer peripheral surface of the combustor liner as a collision jet flows is guided to the upstream side of the combustor liner through the cooling passage between the peripheral wall of the combustor liner and the porous plate. This flow is referred to as "cross flow", and is reused as combustion air or cooling air such as film cooling. It has been confirmed that in such a place where the amount of lateral flow after cooling the impinging jet is large, the impinging force of the jet flowing from the new hole is weakened and the heat transfer coefficient of impingement cooling is lowered.

In order to solve this drawback, various cooling structures have been conventionally proposed. For example, JP-A-6-2130
In No. 02, as shown in FIG. 13, a porous plate b is arranged on the outer peripheral side of the combustor liner a, and a gap therebetween is used as a cooling passage c, and air as a cooling medium is supplied to the cooling passage c as indicated by an arrow d. While circulating, air on the outer peripheral side is jetted from the cooling hole e of the porous plate b toward the inner peripheral side as shown by an arrow f.

The cooling air supply amount is gradually increased in the lateral flow direction g, while the cooling holes e of the perforated plate b are increased.
The pipes h are respectively provided in the pipes so that the height of the pipe h increases in the lateral flow direction g so that the distance between the tip of the pipe h and the peripheral wall of the combustor liner a becomes constant.

As a result, the velocity of the lateral flow of air is made constant, the wall friction loss is reduced, the inflow and jet velocities of air shown by the arrow f are made substantially constant, and the heat transfer coefficient in the cooling section can be kept constant. ing.

Regarding the heat transfer coefficient of cooling by an impinging jet, for example, the kercher & Tabakoff empirical formula (Trans. Of the
Calculated according to ASME Journal of Eng. For power, Jan. 1970, pp73-82). The formula is shown below.

[0008]

[Equation 1] Here, ψ1 is a coefficient determined by the ratio of the cooling hole pitch X and the cooling hole diameter d, ψ2 is a coefficient indicating the influence of the lateral flow, m is an index determined by the ratio of the cooling hole pitch X and the cooling hole diameter d, and is less than 1. It is a value. Further, Re represents the Reynolds number, Pr represents the Prentl number, λ represents the thermal conductivity, and Zn represents the height of the cooling passage.

[0009]

By the way, in recent years, while increasing the temperature from the viewpoint of improving the efficiency of gas turbines, the amount of air that can be consumed for cooling to reduce NOx tends to decrease. There is a demand for a technology that efficiently cools air with a small amount of cooling air. Further, when using a cooling medium other than air, for example, water, steam, fuel, etc., a high-performance cooling technique with a small number of cooling media is required.

Here, according to the equation (1), the cooling hole pitch X, the cooling hole diameter d, and the cooling passage height Z in the practical range.
It can be seen that the heat transfer coefficient increases as the cooling hole diameter d is decreased and the number of cooling holes is increased when the ratio of n is constant and the total amount of cooling air and the velocity are the same. Therefore, in order to improve the cooling efficiency, it is advantageous to arrange a large number of cooling holes having a small diameter.

However, considering the case where the cooling efficiency is improved by using the above-mentioned conventional technique, there are the following problems.

1) Since the jet flow supply pipe h protruding into the cooling passage c increases, the pipe h serves as a flow resistance element, and the pressure loss due to the lateral flow in the cooling passage c increases, and the gas turbine Result in reduced power output and efficiency.

2) When the diameter of the jet h supply pipes h is decreased and the number thereof is increased, since the pipe h has a finite thickness, in order to secure the passage area of the cross flow, the cooling passage height Zn
Need to be higher. Therefore, the height of the pipe h increases, making it difficult to manufacture, and increasing the cost.

3) Similarly, since the ratio of the length and the diameter of the pipe h for supplying the jet flow increases, the strength of the pipe h decreases and the possibility of damaging the pipe h due to vibration or the like increases. Reduce the reliability of.

Therefore, the problem to be solved by the present invention is to use a small amount of cooling medium so that a high cooling effect of the gas turbine combustor can be exhibited, thereby improving the operational reliability of the gas turbine combustor. Is to try.

[0016]

In order to solve the above-mentioned problems, the invention of claim 1 is a gas turbine combustor for cooling a wall surface of a combustor liner, a transition duct or other high temperature portion of a gas turbine from an outer peripheral side. In addition to providing a porous plate surrounding the wall surface that is the cooled part,
In the one in which the cooling medium flowing along the outer peripheral surface of the porous plate is blown out toward the inner peripheral side as a high-speed jet from the holes of the porous plate and collides with the wall surface almost perpendicularly to perform impingement cooling. As a porous plate that surrounds the wall surface that is the portion to be cooled, a corrugated plate having a cylindrical shape as a whole having a plurality of groove portions in the radial direction along the flow direction of the cooling medium is provided, and on the inner peripheral side of this corrugated plate. It is characterized in that a plurality of cooling holes for spraying a cooling medium are provided on the bottom wall of the groove portion projecting toward the wall surface side which is the cooled portion.

According to a second aspect of the present invention, in the cooling structure for a gas turbine combustor according to the first aspect, the cross-sectional area of the groove portion of the corrugated plate is gradually enlarged along the direction of the flow of the cooling medium. To do.

According to a third aspect of the present invention, in the cooling structure for a gas turbine combustor according to the first or second aspect, the bottom wall of the groove portion of the corrugated plate is held at a constant distance from the outer periphery of the wall surface which is the cooled portion. It is characterized by being

According to a fourth aspect of the present invention, in the cooling structure for a gas turbine combustor according to any one of the first to third aspects, the bottom wall of the groove portion of the corrugated plate is curved concentrically with the wall surface as the cooled portion. It is characterized by being a face or a true face.

According to a fifth aspect of the present invention, in the cooling structure for a gas turbine combustor according to any one of the first to fourth aspects, the corrugated plate is provided on a cylindrical outer wall member and an inner peripheral surface of the outer wall member. A plurality of inner wall members with groove portions joined to each other are provided, and the outer wall member is provided with a communication hole communicating with the groove portion of the inner wall member, and the cooling medium is guided to the cooling hole of the bottom wall of the groove portion. And

According to a sixth aspect of the present invention, in the cooling structure for a gas turbine combustor according to any one of the first to fifth aspects, these are provided on the inner peripheral side of the corrugated plate or the outer peripheral side of the wall surface which is the cooled portion. It is characterized in that a pin for setting a gap of a minimum required limit for securing the collision jet height of the cooling medium is provided between the two.

According to a seventh aspect of the present invention, in the cooling structure for a gas turbine combustor according to any one of the first to sixth aspects, an outer peripheral surface of a combustor liner, which is a portion to be cooled from a cooling hole using air as a cooling medium. After it is collided with and is used for cooling,
It is characterized in that the air is introduced into the combustor liner from the upstream side as combustion air.

According to an eighth aspect of the invention, in the cooling structure for a gas turbine combustor according to any one of the first to sixth aspects, cooling is performed by colliding water vapor as a cooling medium from a cooling hole against a wall surface which is a cooled portion. It is characterized in that it is configured to.

According to a ninth aspect of the present invention, in the cooling structure for a gas turbine combustor according to any one of the first to sixth aspects, the gas turbine fuel as a cooling medium is made to collide with a wall surface which is a cooled portion through the cooling holes. It is characterized in that it is configured to be cooled by cooling.

[0025]

BEST MODE FOR CARRYING OUT THE INVENTION Preferred embodiments of a cooling structure for a gas turbine combustor according to the present invention will be described below with reference to the drawings.

1 to 4 show an embodiment in which air is used as a cooling medium to cool the wall surface of the combustor liner, which is the cooled portion. 1 is a diagram showing the overall configuration of a gas turbine combustor, FIG. 2 is a sectional view taken along the line AA of FIG. 1, and FIG. 3 is an enlarged view showing a part of a corrugated plate which is a main part of FIG. FIG. 4 is a cross-sectional view showing, in an enlarged manner, a configuration of a connecting portion of a combustor liner portion and a transition duct of the gas turbine combustor shown in FIG. 1.

The gas turbine combustor 1 has a so-called multi-burner structure of a fuel premixing type, and a fuel nozzle 4 and a burner are provided on one end side (upstream end side) of a cylindrical combustor liner 3 forming the combustion chamber 2. 5 is provided, and a gas turbine (not shown) is connected to the other end side (downstream end side) of the combustor liner 3 via a transition duct 6.

The premixed fuel is burned in the combustion chamber 2 based on the pilot combustion by the burner 5, and the combustion gas is supplied to the gas turbine through the transition duct 6.

The combustor liner 3, the burner 5 and the transition duct 6 are entirely covered with a casing 7. Inside the casing 7, air for combustion and cooling is partially drawn from the compressor 8 side. Is being introduced.

Inside the casing 7, a flow sleeve 9 arranged so as to cover the burner 5 and a combustor liner 3 are provided.
And a corrugated plate 10 that is a porous plate disposed so as to cover the inner surface of the casing 7 is divided into an inner peripheral portion and an outer peripheral portion by the flow sleeve 9 and the corrugated plate 10.

The transition duct 6 is composed of an inner wall 6a, which is a closed wall, and an outer wall 6b having a large number of cooling holes 11 formed therein. The closing plate 12 is provided between the flow sleeve 9 and the corrugated plate 10 and between the corrugated plate 10 and the outer wall 6b of the transition duct 6, respectively.
13 are connected in a sealed state.

2 and 3 show the construction of the corrugated plate 10 in detail. That is, as shown in FIG. 2, the corrugated plate 10 has a number of trapezoidal grooves formed alternately from the outer peripheral side and the inner peripheral side when viewed in a cross section perpendicular to the axis.
It is a one-piece construction in which a cylindrical material is bent in zigzag.
As a result, the corrugated plate 10 has the large-diameter cylindrical wall 14 and the groove portion 15 which is recessed toward the inner peripheral side and extends along the axial direction, and the groove portions 15 are respectively opened on the outer peripheral side and the inner peripheral side. The cross-sectional shape is such that the cross-sectional area gradually increases toward the.

A large number of small-diameter cooling holes 17 are formed in the bottom wall 16 of the groove portion 15, so that the inner peripheral space and the outer peripheral space of the corrugated plate 10 are formed by the large number of cooling holes 17. It is in communication. In addition, the bottom wall 1 of the groove 15
Since 6 is close to the outer peripheral surface of the combustor liner 3, a space having a small radial height Zn is formed between the bottom wall 16 and the combustor liner 3, while the space is formed by the groove portion. They are arranged on both sides of 15 and are surrounded by a large-diameter cylindrical wall 14, and communicate with a wide space having a groove shape opposite to the groove portion 15. In this way, the space between the peripheral wall of the combustor liner 3 and the corrugated plate 10 having an uneven cross-section formed on the outer peripheral side of the combustor liner 3 serves as a cooling air passage, that is, a cooling passage 18, which will be described later.

FIG. 4 shows in detail the structure of the connecting portion of the transition duct 6 on the downstream end side of the combustor liner 3.
The transition duct 6 has the inner wall 6a and the outer wall 6 as described above.
The inner peripheral surface portion of the upstream end of the inner side wall 6a is elastically and hermetically joined to the outer peripheral surface portion of the downstream end of the combustor liner 3 via the spring seal 20. Further, a seal ring 21 is provided on the outer wall 6b of the transition duct 6 so as to extend in the outer peripheral direction, and the seal ring 21 is joined to a mounting plate 23 connected to an end of the corrugated plate 10 via a flow sleeve 22. Is
It is held by the holding plate 24.

A cooling hole 25 for allowing air to flow in from the cooling passage side is provided in the peripheral wall on the downstream end side of the combustor liner 3.
An inner ring 26 for guiding the inflowing air to the downstream transition duct 6 side is provided on the inner peripheral side of the cooling hole 25.

Next, the operation will be described.

The cooling air supplied from the compressor 8 side is supplied around the transition duct 6 on the downstream side of the combustor, as indicated by an arrow m in FIG. This cooling air flows from the cooling holes 11 of the outer peripheral wall 6 a of the transition duct 6 to the inner peripheral side to cool the inner peripheral wall 6 a of the transition duct 6 and flows outside the outer peripheral wall 6 b of the transition duct 6. Flow on the outer periphery of the combustor liner 3 side, that is, on the outer periphery of the corrugated plate 10
Divided into

The air that has cooled the inner peripheral wall 6a of the transition duct 6 flows into the space between the combustor liner 3 and the inner peripheral side of the corrugated plate 10, that is, the cooling passage 18, and further to the upstream side of the combustor liner 3. It flows and is supplied to the combustion chamber 2 as combustion air through the burner 5.

On the other hand, the air flowing to the outer peripheral side of the corrugated plate 10 flows into the groove portion 15 through the opening, and the groove portion 15
It is ejected from the cooling holes 17 of the bottom wall 16 toward the combustor liner 3 and collides with the outer peripheral surface of the combustor liner 3 at a substantially right angle to perform cooling. The distance between the bottom wall 16 of the corrugated plate 10 and the outer peripheral surface of the combustor liner 3 can be set to any value required in design. Further, the diameter of the cooling holes 17 can be set arbitrarily, the pitch of the cooling holes 17 can be set freely on the bottom wall 16, and the collision jet height Zn can also be set arbitrarily. .

Therefore, according to the present invention, a large number of cooling holes 17 having a small diameter can be densely arranged to set an optimum impinging jet flow, so that high cooling performance can be exhibited.

Further, in the cooling passage 18, the transition duct 6
The air used for cooling the air flows in. When this air flows through the cooling passage 18, it collides with the air blown out from the cooling hole 17 of the bottom wall 16 of the groove portion 15 of the corrugated plate 10, but the cooling passage 18 is wide on both sides of the groove portion 15. Since the spaces are in communication with each other, most of the air that has flowed into the cooling passage 18 from the transition duct 6 flows in the wide spaces on both sides of the groove portion 15, so that the air is jetted from the cooling holes 17 and is burned. The degree of impeding the effect of colliding with the outer peripheral surface of the can be suppressed to a very small extent, and a highly efficient cooling effect can be performed.

The air after the jet flow and the air flowing in from the transition duct 6 side are supplied to the upstream side of the combustor liner 3 via the inner peripheral side of the corrugated plate 10 and used for combustion. Since the fluid flows in the wide space on the inner peripheral side of the corrugated plate 10, the pressure loss can be sufficiently reduced. In this case, by setting the cross-sectional shape of the groove portion 15 of the corrugated plate 10, it is possible to suppress the speed of the lateral flow to reduce the pressure loss and prevent the cooling performance from being deteriorated due to the collision jet.

In this embodiment, since the cross-sectional area of the cooling passage 18 is constant in the transverse flow direction, the cooling passage 18
In the inside, the flow velocity gradually increases and a pressure difference is generated, but by setting the cross-sectional area of the groove portion 15 of the corrugated plate 10 sufficiently wide, it is possible to remove the substantial influence on the cooling.

Further, in this embodiment, the corrugated plate 10 is used.
Since the closing plates 12 and 13 are provided at both ends in the axial direction of
There is no unnecessary leakage flow from the outer peripheral side to the inner peripheral side of the corrugated plate 10.

In this embodiment, as shown in FIG. 4, the transition duct 6 and the combustor liner 3 have a structure in which they are overlapped with each other via a spring seal 20. However, the cooling by the impinging jet flow cannot be performed, but since the cooling hole 25 and the inner ring 26 are provided at the downstream end of the combustor liner 3 to perform the film cooling, the same portion can be sufficiently cooled.

Furthermore, in the present embodiment, as shown in FIG. 4, the flow sleeve 22 is provided with a rear portion so that a large amount of air does not flow into the cooling passage 18 from the joint between the outer wall 6b of the transition duct 6 and the flow sleeve 22. Seal ring 21 at the end
Is provided and held by the holding plate 24.
This ensures a pressure difference between the inside and outside of the corrugated plate 10 to increase the velocity of the impinging jet air to enhance the cooling performance.

In the cooling structure of the gas turbine combustor according to the above embodiment, the cooling air for the impinging jet can be supplied from the cooling holes 17 finely arranged with a small diameter, and the impinging jet height can be set to an optimum value. Therefore, high cooling efficiency can be realized.

Further, the cooling passage 18 and the groove portion 15 of the corrugated plate 10 that is a part thereof have a substantially constant shape in the main flow direction of the lateral flow of the air that has cooled the transition duct 6 and the combustor liner 3, and is further designed. Since it is possible to secure a predetermined passage cross-sectional area based on the above, it is possible to reduce the velocity of the lateral flow in the cooling passage 18, so that the pressure loss due to the wall surface friction can be suppressed to be low.

Further, since the transverse flow velocity can be reduced as described above, the cooling performance by the impinging jet flow can be improved. And unlike the prior art, since parts such as fine tubes are unnecessary, the manufacturing cost can be reduced without lowering the reliability of the combustor.

FIG. 5 is a view for explaining another embodiment of the cooling structure for a gas turbine combustor according to the present invention, which is an enlarged sectional view of the corrugated plate 10.

As shown in FIG. 5, in this embodiment, the shape of the corrugated plate 10 which is a main component is improved, and the bottom wall 16 of the groove portion 15 of the corrugated plate 10 is widened to increase the combustor liner. 3 and the corrugated plate 1
The cross-sectional area in the groove portion 15 of the corrugated plate 10 is made wider than that of the embodiment shown in FIG. 2 without increasing the outer diameter of 0 to further reduce the transverse flow velocity.

FIG. 6 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention,
It is sectional drawing which expands and shows the corrugated plate 10.

This embodiment is similar to the structure shown in FIG. 5, except that the large-diameter cylindrical wall 14 of the corrugated plate 10 and the groove portion 1 are formed.
5, the large-diameter cylindrical wall 14 and the component wall 15a of the groove portion 15 are joined by welding, bonding, diffusion joining, or the like so that the corrugated plate 10 can be easily manufactured. It is a thing. In FIG. 6, a pin 27 is provided on the bottom surface of the groove portion 15 of the corrugated plate 10. The pin 27 is provided in order to secure the minimum required collision jet height when the corrugated plate 10 and the combustor liner 3 are thermally deformed. This is applicable to all the embodiments of the present invention, and the pin 27 can be attached to the combustor side.

FIG. 7 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention, which is an enlarged sectional view of the corrugated plate 10.
That is, this embodiment is a modification of the embodiment shown in FIG. 6, in which the large-diameter cylindrical wall 14 of the corrugated plate 10 is a cylindrical plate, and the inner wall of the large-diameter cylindrical wall 14 constitutes the groove 15.
Are joined together. In order to introduce air into the groove 15 of the corrugated plate 10, a hole 28 is formed in the large-diameter cylindrical wall 14.

As shown in FIGS. 6 and 7, the corrugated plate 10 does not have to be one continuous plate in the direction perpendicular to the cross flow (circumferential direction in the embodiment). The gist of the present invention can be achieved if the space on the outer surface is surrounded by corrugations by arbitrarily divided members.

The distance between the bottom walls 16 of the adjacent groove portions 15 of the corrugated plate 10 is set so that the air after cooling has the groove portions 1.
It is effective to arrange a large number of small cooling holes 17 and enhance the cooling performance by making the shape as short as possible while leaving a sufficient distance to flow into the groove 5, and enlarging the cross-sectional area in the groove portion 15 of the corrugated plate 10. It turns out that

The bottom wall 16 of the groove portion 15 of the corrugated plate 10 is shaped so as to maintain a uniform distance from the combustor liner 3, that is, the surface is concentric with the liner 3 due to the collision jet. It is desirable to make the cooling uniform, but as shown in FIG. 5 to FIG. 7, in the case of a large number of repeated waveforms on the circumference, the range in which the cooling performance is sufficiently exhibited even with a non-curved flat surface Is acceptable in. By making the surface flat, manufacturability can be facilitated.

FIG. 8 is a view for explaining another embodiment of the cooling structure for a gas turbine combustor according to the present invention, and FIGS. 8A, 8B and 8C show different axial positions. FIG. 7 is a cross-sectional view showing a state in which the corrugated plate 10 is cut by and the shape of the groove 15 gradually changes in the flow direction of the cooling medium.
In this embodiment, the cross-sectional area of the cooling passage 18 is gradually enlarged in the direction of the lateral flow, and as it advances in the lateral flow direction, as shown in (A), (B), (C) of FIG. In addition, the shape of the groove 15 of the corrugated plate 10 is made deeper in the similar shape in order.

FIG. 9 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention, and FIGS. 9A, 9B and 9C show different axial directions. FIG. 6 is a cross-sectional view showing a state in which the corrugated plate 10 is cut at a position and the shape of the groove 15 gradually changes in the flow direction of the cooling medium. Also in this embodiment, the cross-sectional area of the cooling passage 18 is gradually enlarged in the direction of the lateral flow, and as it proceeds in the direction of the lateral flow, as shown in (A), (B) and (C) of FIG. In addition, the shape of the groove 15 of the corrugated plate 10 is made wider in the similar shape.

8 and 9, the corrugated corner portion is shown as an acute angle, but in reality, the corner portion is formed in an arc shape in order to reduce the pressure loss of the lateral flow in the cooling passage 18. desirable. By thus expanding the cross-sectional area of the cooling passage 18 in the direction of the lateral flow, the velocity of the lateral flow can be made constant, so that the pressure distribution in the cooling passage 18 can be made substantially constant and the combustor can be cooled more uniformly. .

Although air for combustion is used as the cooling medium in the above embodiment, the present invention can be applied to the case of using other cooling medium such as steam or turbine fuel.

For example, FIG. 10 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention. One example of the gas turbine combustor when a cooling medium other than air is used. FIG. 11 is a cross-sectional view showing a portion of FIG.
FIG. 11 is an enlarged sectional view taken along the line BB in FIG. 10.

In these figures, the flow of the cooling medium is shown by the solid arrow s, and the flow of the combustion air is shown by the white arrow t. The end face of the corrugated plate 10 on the cooling passage 18 side is provided with a closing plate 31 on the cooling medium inlet 30 side by a combustor liner 3
On the contrary, the end face on the cooling medium outlet 32 side opposite to the cooling passage 18 is sealed together with the partition wall 34 by the closing plate 33. That is, the cooling medium s is replaced by the air t
The outer peripheral side of the combustor liner 3 is a partition wall 3 so as not to mix with
Surrounded by 4.

With such a structure, the cooling medium s flowing in from the cooling medium inlet 30 is not corrugated plate 10.
It is jetted from the cooling hole 17 to the outer peripheral surface of the combustor liner 3 through the groove portion 15, and is carried out to the cooling medium outlet 32 by the cooling passage 18 including the groove portion 15 of the corrugated plate 10. Since the combustor liner 3 becomes hot and causes thermal expansion, the partition wall 3
It is desirable that the seal plate 4 and the closing plate 33 are not joined by welding or the like, but have a seal structure.

Although the large-diameter cylindrical wall 14 of the corrugated plate 10 and the partition wall 34 are shown in FIG. 11 in close contact with each other,
It is possible to form a space between the large-diameter cylindrical wall 14 and the partition wall 34 to form a part of the cooling medium inflow passage.

FIG. 12 shows the corrugated plate 10 shown in FIG.
It is sectional drawing which shows the modification. In the embodiment shown in FIG. 12, the corrugated plate 10 is formed on the wall 15 a of the groove portion 15.
Only, which is joined to the partition wall 34. As a result, it is possible to save the plate material and reduce the manufacturing cost.

If the casing 7 shown in FIGS. 8 and 9 is replaced with a partition wall 34, the cross-sectional area of the cooling passage 18 is enlarged in the lateral flow direction, and the cooling medium surrounded by the partition wall 34 and the corrugated plate 10 is formed. The inflow passage can be gradually reduced in the lateral flow direction. Therefore, both the speed in the cooling medium inflow passage and the speed in the cooling passage 18 can be made constant, so that the cooling medium can be uniformly distributed from each cooling hole 17,
It is possible to cool the combustor uniformly.

The present invention is not limited to the above embodiments, but can be carried out in various forms. For example, even a ring-type (annular type) combustor can be applied to not only the outer peripheral wall of the combustion chamber but also the inner peripheral wall. Further, the cooling structure of the present invention can be applied not only to the burner liner but also to a transition duct. Furthermore, the cooling holes provided on the bottom wall of the corrugated plate may be arranged in a grid pattern or a staggered pattern, and may be arranged in any manner in consideration of the combustor temperature distribution.

[0069]

As described above in detail, according to the cooling structure of the gas turbine combustor according to the present invention, it becomes possible to supply a jet having a small diameter from a predetermined height position of the bottom wall of the groove portion of the corrugated plate. Since the cooling medium after cooling can flow to the side of the groove portion of the corrugated plate to reduce the transverse flow velocity, the pressure loss in the cooling passage can be reduced, and the heat transfer coefficient of the collision jet flow due to the influence of the transverse flow can be reduced. In addition to being suppressed, it is possible to obtain a high cooling effect by the small diameter jet. Therefore, it becomes possible to exert a high cooling effect of the gas turbine combustor by using a small amount of cooling medium, which can improve the operational reliability of the gas turbine combustor, and also eliminate the need for extra pipes etc. It is possible to achieve the effect of simplifying the configuration by eliminating the need for various components.

[Brief description of drawings]

FIG. 1 is a diagram for explaining an embodiment of a cooling structure of a gas turbine combustor according to the present invention, and an overall configuration diagram showing a partial cross section of the gas turbine combustor.

FIG. 2 is a sectional view taken along the line AA of FIG. 1;

FIG. 3 is an enlarged perspective view showing a part of a corrugated plate, which is a main part of FIG. 1, in a sectional view.

FIG. 4 is an enlarged cross-sectional view showing a configuration of a connecting portion of a combustor liner portion and a transition duct of the gas turbine combustor shown in FIG.

FIG. 5 is a view for explaining another embodiment of the cooling structure of the gas turbine combustor according to the present invention, which is an enlarged cross-sectional view of the corrugated plate.

FIG. 6 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention, which is an enlarged sectional view showing the corrugated plate.

FIG. 7 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention, which is an enlarged sectional view showing the corrugated plate.

FIG. 8 is a view for explaining another embodiment of the cooling structure of the gas turbine combustor according to the present invention, which is (A), (B),
FIG. 6C is a cross-sectional view showing a state in which the corrugated plate is cut at different axial positions and the shape of the groove gradually changes in the flow direction of the cooling medium.

FIG. 9 is a view for explaining still another embodiment of the cooling structure of the gas turbine combustor according to the present invention, (A),
FIGS. 7B and 7C are cross-sectional views showing a state in which the corrugated plate is cut at different axial positions and the shape of the groove gradually changes in the flow direction of the cooling medium.

FIG. 10 is a view for explaining still another embodiment of a cooling structure for a gas turbine combustor according to the present invention, which is a cross section showing a part of the gas turbine combustor when a cooling medium other than air is used. Fig.

11 is an enlarged cross-sectional view taken along the line BB of FIG.

12 is a cross-sectional view showing a modified example of the corrugated plate shown in FIG.

FIG. 13 is a partial cross-sectional view for explaining a conventional technique.

[Explanation of symbols]

 1 Gas Turbine Combustor 2 Combustion Chamber 3 Combustor Liner 4 Fuel Nozzle 5 Burner 6 Transition Duct 6a Inner Side Wall 6b Outer Side Wall 7 Casing 8 Compressor 9 Flow Sleeve 10 Corrugated Plate 11 Cooling Holes 12, 13 Closing Plate 14 Large Diameter Cylindrical Wall 15 Groove 16 Bottom wall 17 Cooling hole 18 Cooling passage 20 Spring seal 21 Seal ring 22 Flow sleeve 23 Mounting plate 24 Holding plate 25 Cooling hole 26 Inner ring 27 pin 28 Hole 30 Cooling medium inlet 31, 33 Closing plate 32 Cooling medium outlet 34 Partition

Claims (9)

[Claims] 1. A cooling structure of a gas turbine combustor for cooling a wall surface of a combustor liner, a transition duct or other high temperature portion of a gas turbine from an outer peripheral side, wherein a porous plate surrounding a wall surface to be cooled is provided. At the same time, the cooling medium flowing along the outer peripheral surface of the porous plate is blown out toward the inner peripheral side as a high-speed jet from the holes of the porous plate and impinges on the wall surface almost vertically to perform impingement cooling. The corrugated plate that has a plurality of grooves in the radial direction along the flow direction of the cooling medium and has a cylindrical shape as a whole is provided as the porous plate that surrounds the wall surface that is the portion to be cooled, and the inner periphery of the corrugated plate A plurality of cooling holes for spraying a cooling medium toward the wall surface side, which is the cooled portion, are provided in the bottom wall of the groove portion projecting toward the side. -Bin combustor cooling structure. 2. The cooling structure for a gas turbine combustor according to claim 1, wherein the cross-sectional area of the groove portion of the corrugated plate is gradually enlarged along the direction of the flow of the cooling medium. Cooling structure. 3. The cooling structure for a gas turbine combustor according to claim 1, wherein the bottom wall of the groove portion of the corrugated plate is held at a certain distance from the outer periphery of the wall surface that is the cooled portion. Cooling structure for a gas turbine combustor. 4. The cooling structure for a gas turbine combustor according to any one of claims 1 to 3, wherein the bottom wall of the groove portion of the corrugated plate is a curved surface or a true surface concentric with the wall surface as the cooled portion. A cooling structure for a gas turbine combustor characterized by being present. 5. The cooling structure for a gas turbine combustor according to any one of claims 1 to 4, wherein the corrugated plate has a cylindrical outer wall member and a groove portion joined to an inner peripheral surface of the outer wall member. Gas turbine combustion characterized by comprising a plurality of inner wall members, wherein the outer wall member is provided with a communication hole communicating with the groove portion of the inner wall member, and the cooling medium is guided to the cooling hole of the bottom wall of the groove portion. Cooling structure. 6. The cooling structure for a gas turbine combustor according to claim 1, wherein a cooling medium is provided on the inner peripheral side of the corrugated plate or on the outer peripheral side of the wall surface that is the cooled portion, between them. Cooling structure for a gas turbine combustor, wherein a pin is provided to set a minimum necessary clearance for ensuring the height of the collision jet flow. 7. The cooling structure for a gas turbine combustor according to any one of claims 1 to 6, wherein the cooling medium is used as air to collide with the outer peripheral surface of the combustor liner, which is the cooled portion, from the cooling hole. A cooling structure for a gas turbine combustor, wherein after cooling, the air is introduced into the combustor liner from the upstream side as combustion air. 8. The cooling structure for a gas turbine combustor according to any one of claims 1 to 6, wherein steam is collided from a cooling hole as a cooling medium to a wall surface which is a cooled portion to cool it. A cooling structure for a gas turbine combustor. 9. The cooling structure for a gas turbine combustor according to any one of claims 1 to 6, wherein the gas turbine fuel as a cooling medium is made to collide with a wall surface, which is a cooled portion, from a cooling hole to cool the gas turbine fuel. A cooling structure for a gas turbine combustor characterized by the above.