JP2011089462A - Cooling structure of combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a cooling structure of a combustor capable of enhancing inner wall cooling efficiency with smaller labor and at low costs. <P>SOLUTION: The cooling structure 6 of the combustor has a plurality of first grooves 51 formed at the inner wall 5 at its outer wall 4 side and extending in a prescribed direction parallel with one another, a plurality of second grooves part 52 formed at the inner wall 5 at its the outer wall 4 side and extending in a direction intersecting the first grooves 51 in such a way as being parallel with one another, and a plurality of radiation parts 53 provided at the inner wall 5 in such a way as being surrounded by the first grooves 51 and the second grooves 52 and protruding toward the outer wall 4, and is configured so that a hole 41 is formed in a position facing the first grooves 51 or the second grooves 52, and a gap S4 of a certain size is formed between the forefront parts 53a of the radiation parts 53 and the outer wall 4. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

 The present invention relates to a cooling structure for a combustor suitable for use in a combustor such as a gas turbine.

 Conventionally, a cooling structure that cools the surface of a member exposed to high-temperature combustion gas is used in a gas turbine or the like. An example of such a cooling structure is an impingement cooling structure that uses a double wall structure. A double wall consists of a high temperature side wall part exposed to combustion gas, and a low temperature side wall part which is arranged on the opposite side to the region where the high temperature side wall part is spaced from the region where the combustion gas flows. Impingement cooling is performed by introducing a cooling fluid (such as air) into the space as a jet through a plurality of holes provided in the low temperature side wall, and causing the cooling fluid to collide with the high temperature side wall. The part is cooled.

 Further, as a cooling structure used together with the impingement cooling structure, a structure in which a heat radiating portion that is integrally connected to the high temperature side wall portion and protrudes into the space is employed. When the cooling fluid after colliding with the high temperature side wall portion comes into contact with the surface of the heat radiating portion, the heat transmitted from the high temperature side wall portion can be actively dissipated to cool the high temperature side wall portion.

 Here, Patent Document 1 discloses a turbine blade having the above-described double wall structure and used in a gas turbine. As a method of manufacturing a turbine blade having a double wall structure, the double wall structure has a complicated shape having a plurality of heat radiating portions and holes, and the outer shape of the turbine blade is relatively small. A casting method is generally used.

JP-A-11-62504

However, the following problems exist in the above-described prior art.
A combustor in a gas turbine has a combustion region for burning fuel therein, and an inner wall of the combustor provided surrounding the combustion region is exposed to high-temperature combustion gas. In order to prevent such heat damage on the inner wall, a cooling structure using a double wall structure is also used in the combustor. In addition, in gas turbines, the temperature of combustion gas tends to rise due to demand for higher output and higher performance.

 Here, in order to cope with an increase in the temperature of the combustion gas, in the cooling structure using the double wall structure, it is conceivable to perform not only impingement cooling but also cooling by installing the heat dissipating section described above. However, since the outer shape of the combustor is large, it is difficult to form the inner wall by a casting method, and providing a plurality of heat radiating portions one by one on the inner wall by machining or the like requires a great deal of manufacturing effort and There was a problem that it was costly.

 The present invention has been made in consideration of the above points, and an object of the present invention is to provide a cooling structure for a combustor that can further improve the cooling efficiency of the inner wall with less effort and cost.

In order to solve the above problems, the present invention employs the following means.
The cooling structure of the combustor according to the present invention has an inner wall that forms a combustion region of fuel, and an outer wall that is spaced from the inner wall and disposed on the opposite side of the combustion region across the inner wall. A cooling structure for a combustor in which a fluid is introduced into the space through a plurality of holes provided in an outer wall to cool the inner wall, and is provided on the outer wall side of the inner wall and extends in parallel with each other in a predetermined direction. A plurality of first groove portions, a plurality of second groove portions provided on the outer wall side of the inner wall and extending in parallel with each other in a direction intersecting the first groove portion, a plurality of first groove portions and a plurality of second groove portions on the inner wall And a plurality of heat dissipating portions protruding toward the outer wall, the hole portion being provided at a position facing the first groove portion or the second groove portion, and between the front end portion of the heat dissipating portion and the outer wall. Adopts a configuration in which a predetermined amount of gap is formed.
In the present invention employing such a configuration, it is possible to easily form a plurality of first groove portions and second groove portions on the outer wall side surface of the inner wall using cutting or the like, so that the cooling efficiency of the inner wall is further increased. It becomes possible to form the heat radiating part for improving without excessively increasing the labor and cost of formation. Further, in the present invention, since a predetermined amount of gap is formed between the distal end portion of the heat radiating portion and the outer wall, the heat radiating portion and the outer wall are caused by a difference in thermal expansion between the inner wall and the outer wall. Can be prevented from being touched or damaged.

The combustor cooling structure according to the present invention has a plurality of second hole portions that face the first groove portion or the second groove portion and that are provided on the inner wall in a non-opposing positional relationship with the hole portion and penetrate in the plate thickness direction. The configuration is adopted.
In the present invention employing such a configuration, the cooling fluid introduced into the space flows to the surface on the combustion region side of the inner wall via the second hole, and the film-like flow of the cooling fluid flows on the surface. Is formed.

Further, in the cooling structure of the combustor according to the present invention, the heat dissipating part is a quadrangular prism, the hole part faces the first groove part, and is disposed at a position excluding the intersection part of the first groove part and the second groove part. A configuration is adopted in which the hole portion faces the second groove portion and is disposed at a position excluding the intersecting portion.
In the present invention employing such a configuration, the cooling fluid introduced into the first groove portion through the hole portion flows along the side surface of the heat radiating portion provided on the inner wall. Therefore, it becomes possible to improve the cooling efficiency of the inner wall. In the present invention, the cooling fluid introduced from the pair of adjacent holes in the extending direction of the first groove collides with each other at the intersection, but quickly enters the second groove that intersects the first groove. To be introduced. Therefore, the influence of the cross flow on the cooling fluid is reduced.

In the combustor cooling structure according to the present invention, the heat dissipating part is a quadrangular prism, and the hole part faces one of the pair of first groove parts surrounding the predetermined heat dissipating part and the pair of first enclosing heat dissipating parts. The second hole portion is disposed at a position facing one of the two groove portions, and the second hole portion is facing the other of the pair of first groove portions and a position facing the other of the pair of second groove portions, respectively. Adopting the configuration of being arranged.
In the present invention employing such a configuration, the cooling fluid introduced into the first groove portion and the second groove portion through the hole portion flows along the side surface of the heat radiating portion provided on the inner wall. Therefore, it becomes possible to improve the cooling efficiency of the inner wall. Further, in the present invention, the cooling fluid introduced from the pair of holes disposed so as to face the first groove and the second groove surrounding the predetermined heat radiating portion is formed between the first groove and the second groove. Although they collide with each other at the intersection, they are promptly introduced into the first and second grooves on the opposite side across the intersection. Therefore, the influence of the cross flow on the cooling fluid is reduced.

In the cooling structure of the combustor according to the present invention, the heat radiating portion is a quadrangular prism, and the hole and the second hole are located at a position facing the intersection of the first groove and the second groove, and the predetermined first A configuration is adopted in which the groove portions and the predetermined second groove portions are alternately arranged in the extending directions.
In the present invention employing such a configuration, the cooling fluid introduced into the intersecting portion through the hole flows along the side surface of the heat radiating portion provided on the inner wall. Therefore, it becomes possible to improve the cooling efficiency of the inner wall. In the present invention, the cooling fluid introduced from the predetermined hole is introduced into the second hole without substantially intersecting with the cooling fluid introduced from the other hole. Therefore, the influence of the cross flow on the cooling fluid is reduced.

Further, in the combustor cooling structure according to the present invention, the inner wall is formed in a substantially cylindrical shape, and the first groove portion or the second groove portion is disposed substantially parallel to the central axis of the substantially cylindrical inner wall. Adopt the configuration.
In the present invention adopting such a configuration, when a substantially cylindrical inner wall is formed by bending a plate-like member in which the first groove portion and the second groove portion are formed, it is possible to bend easily and substantially. The stress remaining on the cylindrical inner wall is reduced.

According to the present invention, the following effects can be obtained.
According to the present invention, there is an effect that a combustor cooling structure that can further improve the cooling efficiency of the inner wall can be provided with less effort and cost.

1 is a schematic diagram showing a configuration of a combustor 1. FIG. 3 is a schematic view showing configurations of an outer wall 4, a liner 5, and a cooling structure 6. FIG. 10 is a schematic diagram showing a first modification example regarding the arrangement of the hole 41 and the second hole 54. FIG. 11 is a schematic diagram showing a second modification example regarding the arrangement of the hole 41 and the second hole 54.

 Hereinafter, an embodiment of a cooling structure for a combustor according to the present invention will be described with reference to FIGS. 1 to 4. In each drawing used for the following description, the scale of each member is appropriately changed to make each member a recognizable size.

FIG. 1 is a schematic diagram showing a configuration of a combustor 1 according to the present embodiment.
The combustor 1 is provided in a gas turbine (not shown), and generates combustion gas H by burning fuel in a combustion region S1 formed in the combustor 1. This combustion gas H is used to drive a turbine (not shown) provided on the downstream side of the combustor 1.
The combustor 1 is a so-called annular type combustor, and has a substantially annular shape. Therefore, the combustion region S1 formed in the combustor 1 is also formed in a substantially annular shape. The combustor 1 is disposed in an air flow space S <b> 2 formed between the outer casing 100 and the inner casing 200 of the gas turbine. Compressed air G compressed by a compression portion (not shown) of the gas turbine flows in the air flow space S2, and this compressed air G is used for combustion of fuel, cooling of the combustor 1, and the like. .

The combustor 1 includes a fuel injection unit 2, an air introduction unit 3, an outer wall 4, a liner (inner wall) 5, and a cooling structure 6 (see FIG. 2).
The fuel injection unit 2 is for injecting and introducing fuel into the combustion region S1. The fuel injection unit 2 is connected to a fuel storage unit (not shown) provided outside the air flow space S2.
The air introduction part 3 is provided adjacent to the fuel injection part 2, and introduces the compressed air G in the air flow space S2 into the combustion region S1.

The outer wall 4 is a member constituting the outer wall of the substantially annular combustor 1, and has a substantially cylindrical shape disposed on the opposite side of the combustion region S <b> 1 across the liner 5, that is, on the inner and outer peripheral surfaces of the combustor 1. It is a plate member.
The liner 5 is configured by arranging substantially cylindrical plate members having different diameters on the inside and outside in the radial direction, and forms a substantially annular combustion region S1 between the inside and outside plate members. is there. That is, the liner 5 is in contact with the high-temperature combustion gas H. Moreover, the outer wall 4 is arrange | positioned so that the liner 5 may be enclosed from the inner peripheral surface side, and the outer wall 4 and the liner 5 comprise the double wall structure.

 The cooling structure 6 is a structure for cooling the liner 5 in the combustor 1. The cooling structure 6 has a part of the elements constituting the outer wall 4 and the liner 5.

Next, the configuration of the outer wall 4, the liner 5 and the cooling structure 6 will be described in detail with reference to FIG.
2A and 2B are schematic views showing configurations of the outer wall 4, the liner 5, and the cooling structure 6, wherein (a) is a perspective view and (b) is a plan view of the liner 5.
As shown in FIG. 2, the outer wall 4 and the liner 5 are connected via a plurality of connecting members (not shown), and are provided to face each other with a wall space (space) S3.

The outer wall 4 has a plurality of holes 41.
The hole 41 is a hole that is provided so as to penetrate in the thickness direction of the outer wall 4 and communicates the air flow space S2 that is the external space of the combustor 1 and the wall space S3. The hole 41 faces a first groove 51 described later provided in the liner 5 and is disposed at a position excluding an intersection 55 between the first groove 51 and a second groove 52 described later.

The liner 5 has a plurality of first groove portions 51, second groove portions 52, heat radiation portions 53, and second hole portions 54.
The plurality of first groove portions 51 are groove portions that are provided on the outer wall 4 side of the liner 5 and extend in parallel to each other in a direction orthogonal to the central axis of the liner 5 formed in a substantially cylindrical shape.

 The plurality of second groove portions 52 are provided on the outer wall 4 side of the liner 5 and extend in parallel to each other in a direction intersecting the first groove portion 51 (orthogonal in the present embodiment). The second groove 52 extends in parallel with the central axis of the liner 5 that is formed in a substantially cylindrical shape. A location where the first groove portion 51 and the second groove portion 52 intersect with each other is defined as an intersecting portion 55, and a bottom surface of the liner 5 facing the outer wall 4 of the first groove portion 51 and the second groove portion 52 is defined as a first wall surface 5a. A surface opposite to the first wall surface 5a, that is, a surface facing the combustion region S1 of the liner 5 is defined as a second wall surface 5b.

 The plurality of heat radiating portions 53 are used for cooling the liner 5, are surrounded by the plurality of first groove portions 51 and the plurality of second groove portions 52, are provided in the liner 5, and protrude toward the outer wall 4. It is a quadrangular prism with a plan view.

In order to form the liner 5 having the first groove portion 51, the second groove portion 52, and the heat radiating portion 53, first, a substantially straight line is formed by general cutting or the like on a predetermined plate member (not shown). A first groove portion 51 and a second groove portion 52 are formed. Therefore, the formation can be easily performed with less labor and cost. By forming the first groove portion 51 and the second groove portion 52, a prismatic heat dissipation portion 53 and a first wall surface 5a surrounded by the groove portions 51 and 52 are formed. Further, after forming the first groove 51 and the second groove 52, the liner 5 is bent by bending the plate member around a predetermined axis located on the second wall surface 5b side and parallel to the extending direction of the second groove 52. Can be molded.
As described above, since the plurality of heat radiation parts 53 can be formed without using a casting method or the like, the heat radiation part 53 for further improving the cooling efficiency of the liner 5 is excessively increased in labor and cost. It can form without.

 Further, in this embodiment, the liner 5 bends the plate member around a predetermined axis parallel to the extending direction of the second groove portion 52. Therefore, the plate member can be easily bent, and after molding. The stress remaining in the liner 5 is reduced, and deformation or breakage caused by the stress can be prevented.

A gap S4 is formed between the distal end portion 53a of the heat radiating portion 53 and the outer wall 4. Therefore, it is possible to prevent problems such as contact and breakage between the heat radiating portion 53 and the outer wall 4 due to a difference in thermal expansion between the outer wall 4 and the liner 5.
The side surface 53 b of the heat radiating portion 53 is provided in parallel with the facing direction of the outer wall 4 and the liner 5.

 The plurality of second holes 54 are holes that face the second groove 52 and are provided in the liner 5 in a positional relationship that does not face the intersection 55 and penetrate in the thickness direction. That is, the second hole portion 54 is a hole portion that communicates the wall space S3 and the combustion region S1.

 The cooling structure 6 is a structure for cooling the liner 5, and includes a part of the elements constituting the outer wall 4 and the liner 5, and includes the outer wall 4, the hole 41, and the liner 5. And a first groove 51, a second groove 52, a heat dissipation part 53, and a second hole 54.

Next, the cooling action of the cooling structure 6 according to this embodiment will be described with reference to FIG.
The compressed air G is flowing in the air flow space S2. Since the pressure of the compressed air G is higher than the pressure of the combustion gas H in the combustion region S1, a flow of the compressed air G from the outer wall 4 toward the liner 5 occurs due to the pressure difference. That is, the compressed air G is introduced into the wall space G3 through the hole 41. Further, due to the pressure difference between the air flow space S2 and the wall space S3, the compressed air G is vigorously discharged from the hole 41 and is introduced into the wall space S3 as a jet (fluid) G2.

 The jet G2 introduced into the wall space S3 flows in the first groove 51 toward the liner 5 and collides with the first wall surface 5a facing the outer wall 4. Here, the liner 5 is heated by the combustion gas H flowing in the combustion region S1, and since the temperature of the jet G2 is lower than the temperature of the liner 5, the jet G2 collides with the first wall surface 5a to cause the jet G2. And the first wall surface 5a exchange heat, and the liner 5 is cooled by the jet G2 (impingement cooling).

 The jet G2 becomes a post-collision flow G3 after colliding with the first wall surface 5a. The post-collision flow G3 flows along the extending direction of the first groove 51 from the location where it collides with the first wall surface 5a. That is, since the post-collision flow G3 flows along the side surface 53b of the heat radiating portion 53 provided in the liner 5, the heat radiating portion 53 can be cooled by the post-collision flow G3, and the cooling efficiency of the liner 5 having the heat radiating portion 53 Can be further improved.

 In addition, the post-impact flow G3 introduced from a pair of adjacent holes 41 in the extending direction of the first groove 51 and colliding with the first wall surface 5a flows along the first groove 51 and intersects 55. Although they interfere with each other, they are promptly introduced into the second groove 52 that intersects the first groove 51. Therefore, the after-collision flow G3 that interfered with each other at the intersection 55 hardly flows back to the jet flow G2, and the influence of the after-collision flow G3 on the jet flow G2, that is, the influence of the cross flow can be reduced. Therefore, the cooling efficiency of the liner 5 by impingement cooling can be further improved.

The post-impact flow G3 that has flowed into the second groove 52 flows along the side surface 53b of the heat radiating portion 53, and the heat radiating portion 53 can be cooled by the post-collision flow G3.
Further, the post-impact flow G3 flows into the combustion region S1 through the second hole portion 54 provided facing the second groove portion 52. Since a plurality of second holes 54 are formed in the liner 5, the post-impact flow G3 that has flowed to the second wall surface 5b side of the liner 5 merges with another adjacent post-collision flow G3, along the second wall surface 5b. Thus, a film-like flow G4 is obtained. This film-like flow G4 cools the liner 5 from the second wall surface 5b side, and can suppress the heat of the combustion gas H from being transmitted to the liner 5 (film cooling). The film-like flow G4 flows downstream along with the combustion gas H, and is discharged to the outside after passing through an installation location of a turbine blade (not shown).

Therefore, according to the present embodiment, the following effects can be obtained.
There is an effect that the cooling structure 6 of the combustor 1 that can further improve the cooling efficiency of the liner 5 can be provided with less effort and cost.

 As described above, the preferred embodiments according to the present invention have been described with reference to the accompanying drawings, but the present invention is not limited to the examples. Various shapes, combinations, and the like of the constituent members shown in the above-described examples are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

 For example, in the above-described embodiment, the second hole 54 is formed to cool the film to the liner 5, but the present invention is not limited to this, and the impingement is not performed without forming the second hole 54. It is also possible to employ a configuration in which only the cooling of the heat sink and the cooling of the heat radiating portion 53 is performed. In this case, the hole 41 is provided at a position facing either the first groove 51 or the second groove 52.

 Moreover, in the said embodiment, although the combustor 1 was an annular type combustor, it is not limited to this, The canister type combustor formed in the substantially cylindrical shape may be sufficient.

Moreover, it is good also considering the arrangement | positioning of the hole 41 and the 2nd hole 54 in the said embodiment as the positional relationship shown in FIG.
FIG. 3 is a schematic diagram illustrating a first modification example regarding the arrangement of the hole 41 and the second hole 54.
The hole 41 is disposed at a position facing one of the pair of first groove portions 51 surrounding the predetermined heat radiating portion 53 and a position facing one of the pair of second groove portions 52 surrounding the heat radiating portion 53. The second hole portion 54 is disposed at a position facing the other of the pair of first groove portions 51 and a position facing the other of the pair of second groove portions 52.
Even with such a configuration, the influence of the cross flow on the jet G2 can be reduced.

Moreover, it is good also considering the arrangement | positioning of the hole 41 and the 2nd hole 54 in the said embodiment as the positional relationship shown in FIG.
FIG. 4 is a schematic diagram illustrating a second modification example regarding the arrangement of the hole 41 and the second hole 54.
The hole 41 and the second hole 54 are alternately arranged at positions facing the intersecting portion 55 and with respect to the extending directions of the first groove 51 and the second groove 52.
Even with such a configuration, the influence of the cross flow on the jet G2 can be reduced.

 Moreover, in the said embodiment, although the thermal radiation part 53 was a square pole, a polygonal prism, for example, a triangular prism, may be sufficient. In this case, a plurality of third groove portions that intersect with both the first groove portion 51 and the second groove portion 52 and extend in parallel with each other are formed in the liner 5.

 Moreover, in the said embodiment, although the thermal radiation part 53 was a square pillar of the planar view rectangle, the square pillar of a planar view and a parallelogram may be sufficient as it.

 Moreover, in the said embodiment, although air is used as a fluid for cooling the liner 5, you may use other fluids, such as an inert gas, for example.

4 ... outer wall, 41 ... hole, 5 ... liner (inner wall), 51 ... first groove, 52 ... second groove, 53 ... heat dissipation part, 53a ... tip part, 54 ... second hole, 55 ... crossing part, 6 ... Cooling structure, G2 ... Jet (fluid), S1 ... Combustion region, S3 ... Wall space (space), S4 ... Gap

Claims (6)

An inner wall that forms a combustion region of fuel, and an outer wall that is spaced from the inner wall and disposed on the opposite side of the combustion region with the inner wall interposed therebetween, and a cooling fluid is provided on the outer wall A cooling structure of a combustor that is introduced into the space through a plurality of holes and cools the inner wall;
A plurality of first grooves provided on the outer wall side of the inner wall and extending parallel to each other in a predetermined direction;
A plurality of second groove portions provided on the outer wall side of the inner wall and extending in parallel with each other in a direction crossing the first groove portion;
A plurality of heat dissipating portions provided on the inner wall surrounded by the plurality of first groove portions and the plurality of second groove portions, and projecting toward the outer wall;
The hole is provided at a position facing the first groove or the second groove,
A cooling structure for a combustor, wherein a predetermined amount of gap is formed between a front end portion of the heat radiating portion and the outer wall. The combustor cooling structure according to claim 1,
A combustor comprising a plurality of second hole portions facing the first groove portion or the second groove portion and provided in the inner wall in a positional relationship not facing the hole portion and penetrating in a plate thickness direction. Cooling structure. The cooling structure for a combustor according to claim 2,
The heat dissipating part is a square pole,
The hole portion is disposed at a position facing the first groove portion and excluding an intersection between the first groove portion and the second groove portion,
The combustor cooling structure according to claim 1, wherein the second hole portion is disposed at a position facing the second groove portion and excluding the intersecting portion. The cooling structure for a combustor according to claim 2,
The heat dissipating part is a square pole,
The hole is located at a position facing one of the pair of first groove portions surrounding the predetermined heat radiating portion, and at a position facing one of the pair of second groove portions surrounding the predetermined heat radiating portion. Arranged,
The combustor, wherein the second hole portion is disposed at a position facing the other of the pair of first groove portions and a position facing the other of the pair of second groove portions. Cooling structure. The cooling structure for a combustor according to claim 2,
The heat dissipating part is a square pole,
The hole portion and the second hole portion are located at a position facing an intersection of the first groove portion and the second groove portion, and with respect to respective extending directions of the predetermined first groove portion and the predetermined second groove portion. Combustor cooling structure characterized by being arranged alternately. In the cooling structure of the combustor according to any one of claims 1 to 5,
The inner wall is formed in a substantially cylindrical shape,
The combustor cooling structure according to claim 1, wherein the first groove portion or the second groove portion is disposed substantially parallel to a central axis of the substantially cylindrical inner wall.

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