JP2019184157A - Cooling structure and combustor - Google Patents

Abstract

To provide a cooling structure for supplying cooling fluid to a wall part uniformly.SOLUTION: Cooling air flowing into a combustor liner 2b is diffused in the circumferential direction via a diffusion member 2d provided downstream of a cooling hole 2f. Therefore, the diffusion member 2d uniformizes the flow speed and flow rate of the cooling air flowing into the combustor liner 2b in the circumferential direction of the combustor liner 2b, so as to cool the wall surface of the combustor liner 2b uniformly. Since a louver 2e is provided in the vicinity of the cooling hole 2f, the cooling air flowing into from the diffusion member 2d can be guided along the inner wall surface of the combustor liner 2b, and thus the inner wall surface of the combustor liner 2b can be cooled effectively.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a cooling structure and a combustor.

  For example, Patent Document 1 discloses a cooling structure for a combustor. In the combustor, a plurality of cooling holes are formed. Through this cooling hole, a part of the air supplied for combustion is introduced into the combustor as cooling air, thereby cooling the inner wall of the combustor so as not to reach a high temperature exceeding the allowable temperature.

JP 2012-31737 A

  The cooling in the structure as described above is performed by the cooling fluid that flows in from the cooling holes formed in the wall. However, the fluid flowing in from the cooling hole tends to have a high flow rate in a region near the cooling hole in a direction intersecting the fluid flow direction, and a low flow rate in a region away from the cooling hole. That is, the flow rate of the cooling fluid on the wall surface of the structure is distributed depending on the formation position of the cooling holes. Such a distribution of the flow rate of the cooling fluid causes a temperature distribution on the wall surface.

  The present invention has been made in view of the above-described problems, and an object thereof is to uniformly supply a cooling fluid to a wall portion.

  In order to achieve the above object, according to the present invention, as a first means related to a cooling structure, a cooling structure that cools a wall portion of a structure, which is downstream of cooling holes formed in the wall portion and A means is provided that includes a porous diffusion member that is provided on the wall surface and through which the cooling fluid can pass.

  As a second means related to the cooling structure, a means is adopted in which, in the first means, the diffusion member is a sintered metal.

  As the third means related to the cooling structure, the means of the first or second means is provided with a louver provided on the wall portion and guiding the cooling fluid along the wall surface.

  As the fourth means related to the cooling structure, in the third means, the cooling hole is provided on a flow path of the cooling fluid formed by the louver and the wall surface.

  As a first means related to the combustor, comprising a combustor liner in which a plurality of cooling holes are formed in the circumferential direction, and the cooling structure according to any one of claims 1 to 4, wherein the diffusion member is A means of being provided on the inner wall surface of the combustor liner is employed.

  As the second means related to the combustor, a means is adopted in which, in the first means, the diffusion member is annularly set.

  According to the present invention, the cooling fluid flowing in from the cooling hole is diffused in the structure through the diffusion member. Therefore, the flow velocity and flow rate of the cooling fluid flowing into the structure are made uniform in the direction crossing the flow direction of the structure, and the cooling fluid can be uniformly supplied to the wall portion of the structure. It is.

It is a lineblock diagram of the gas turbine in one embodiment of the present invention. It is a model perspective view showing a part of combustor liner in one embodiment of the present invention. It is a perspective view of the diffusion member with which the combustor in one embodiment of the present invention is provided.

  As shown in FIG. 1, the gas turbine G includes a compressor 1, a combustor 2, and a turbine 3. The compressor 1 includes a compressor rotor blade 1a, a compressor stationary blade 1b, and a housing 1c. The compressor 1 compresses and pressurizes the outside air taken in from the intake port H1 between a compressor blade 1a fixed to a turbine shaft 3a, which will be described later, and a compressor stationary blade 1b fixed to the housing 1c. Thus, the compressed air chamber R1 in which the combustor 2 is disposed is supplied.

  The combustor 2 includes a fuel supply nozzle 2a, a combustor liner 2b, a swirler 2c, a diffusion member 2d, and a louver 2e. The combustor 2 burns a mixed gas of fuel supplied via the fuel supply nozzle 2a and compressed air supplied from the compressor 1 in a combustion region R2 formed by the combustor liner 2b, and the combustion The gas is supplied to the turbine 3.

  The turbine 3 includes a turbine shaft 3a, a turbine rotor blade 3b, and a turbine stationary blade 3c. The turbine 3 obtains rotational kinetic energy from the combustion gas supplied from the combustor 2 by a turbine blade 3b fixed to the turbine shaft 3a and rotatable, and a turbine stationary blade 3c fixed to the housing 1c. The combustion gas that has passed through the blades is exhausted to the outside through the exhaust port H2.

  As shown in FIG. 1, the combustor 2 is installed in the compressed air chamber R1. The compressed air chamber R1 is provided in the housing 1c and forms an annular space around the turbine shaft 3a. The combustor 2 includes a so-called annular combustor liner 2b, a swirler 2c, a diffusing member 2d, and a louver 2e that have a substantially annular shape along the annular space of the compressed air chamber R1. A fuel supply nozzle 2a is connected to the side of the combustor liner 2b to which compressed air is supplied from the compressor 1. A plurality of fuel supply nozzles 2a are connected to the annular combustor liner 2b at predetermined intervals. A swirler 2c is provided around the fuel supply nozzle 2a.

  The combustor liner 2b has a substantially cylindrical shape, and a plurality of cooling holes 2f are formed along the circumferential direction. The cooling holes 2f are through holes that communicate the inside and the outside of the combustor liner 2b, and are provided at equal intervals along the circumferential direction of the combustor liner 2b. A number of cooling holes 2f are provided in the circumferential direction of the combustor liner 2b, and a plurality of stages are provided in the axial direction of the combustor liner 2b.

  The swirler 2c is configured to introduce the compressed air supplied from the compressor 1 into the combustion region R2 from the vicinity of the fuel supply nozzle 2a to generate a mixed gas.

  The diffusing member 2d has an arc shape formed by dividing a substantially annular member into four parts. The diffusing member 2d is an inner wall surface of the combustor liner 2b and is provided in the vicinity of the cooling hole 2f and on the downstream side and between the louver 2e and the combustor liner 2b. The diffusion member 2d of the present embodiment is a porous member made of sintered metal and having a plurality of pores and cavities formed therein. Further, the diffusion member 2d divided into four forms an annular shape by being fixed to the combustor liner 2b in a contact state with each other when attached to the combustor liner 2b. The diffusion member 2d has a shape along the inner wall surface of the combustor liner 2b. The diffusing member 2d is substantially rectangular in a cross section along the axial direction.

  As shown in FIG. 2, the louver 2e is provided on the inner wall surface of the combustor liner 2b along the cooling hole 2f in a circumferential direction and in the downstream direction of the combustion air. Thereby, the louver 2e covers the cooling hole 2f and the diffusion member 2d in the circumferential direction of the combustor liner 2b. A gap is formed between the louver 2e and the inner wall surface of the combustor liner 2b, and cooling air (cooling fluid) is guided along the inner wall surface of the combustor liner 2b by the gap. A diffusion member 2d is disposed in the gap between the louver 2e and the inner wall surface of the combustor liner 2b. The louver 2e is formed with a groove over the entire circumference on the surface facing the combustor liner 2b side. By fixing the louver 2e with the diffusing member 2d fitted in the groove, the louver 2e comes into contact with the diffusing member 2d over the entire circumference.

  Such diffusion member 2d and louver 2e correspond to the cooling structure in the present invention. Further, the wall portion of the combustor liner 2b corresponds to the wall portion of the structure in the present invention.

  Then, the effect | action of the diffusion member 2d in the combustor liner 2b which concerns on such this embodiment is demonstrated.

  When combustion is performed in the combustor 2, the cooling air flows from the compressed air chamber R1 into the combustor liner 2b through the cooling holes 2f. At this time, the cooling air flowing into the combustor liner 2b flows toward the downstream side along the wall surface of the combustor liner 2b through the gap between the louver 2e and the combustor liner 2b. A diffusion member 2d is provided in the gap, and the cooling air flowing into the combustor liner 2b passes through the diffusion member 2d. The cooling air is dispersed in the circumferential direction of the combustor liner 2b by passing through a plurality of cavities and pores formed inside in the diffusion member 2d. Then, when the cooling air passes through the pores of the diffusion member 2d, it is diffused toward the outside in the radial direction of the pores, thereby diffusing in the circumferential direction of the combustor liner 2b. Thereby, the cooling air downstream of the diffusing member 2d has a uniform flow velocity and flow rate in the circumferential direction of the combustor liner 2b.

  The wall surface of the combustor liner 2b is cooled by the cooling air flowing along the wall surface of the combustor liner 2b. Thereafter, the cooling air is discharged from the downstream end of the combustor liner 2b.

  According to the present embodiment, the cooling air flowing into the combustor liner 2b is diffused in the circumferential direction through the diffusion member 2d provided on the downstream side of the cooling hole 2f. Therefore, the diffusion member 2d equalizes the flow velocity and flow rate of the cooling air flowing into the combustor liner 2b in the circumferential direction of the combustor liner 2b, and the wall surface of the combustor liner 2b is uniformly cooled.

  In addition, according to the present embodiment, by using a sintered metal as the diffusing member 2d, it is possible to ensure the strength while providing a porous structure.

  Further, according to the present embodiment, the louver 2e is provided in the vicinity of the cooling hole 2f, and it is possible to guide the cooling air flowing in from the diffusion member 2d along the inner wall surface of the combustor liner 2b. Therefore, the inner wall surface of the combustor liner 2b can be effectively cooled.

  Further, according to the present embodiment, the louver 2e is provided in contact with the diffusion member 2d. That is, the diffusion member 2d is in contact with each of the louver 2e and the inner wall surface of the combustor liner 2b. Thereby, the cooling air flowing in from the cooling hole 2f can easily pass through the diffusion member 2d. Therefore, the diffusion effect by the diffusing member 2d can be further enhanced.

  Furthermore, the diffusing member 2d is provided on the entire circumference along the inner wall surface of the combustor liner 2b. Thereby, the diffusion member 2d can be allowed to pass through the cooling air flowing in from any cooling hole 2f, and the diffusion effect by the diffusion member 2d can be further enhanced.

In addition, this invention is not limited to the said embodiment, For example, the following modifications can be considered.
(1) In the above embodiment, the diffusing member 2d is provided so as to contact the louver 2e and the inner wall surface of the combustor liner 2b and fill the gap between the louver 2e and the inner wall surface of the combustor liner 2b. However, the present invention is not limited to this. The diffusing member 2d may be provided with a gap between the diffusing member 2d and the louver 2e. In this case, more cooling air can be taken into the combustor liner 2b.

(2) In the above embodiment, the configuration in which the louver 2e is provided has been described, but the present invention is not limited to this. In the combustor liner 2b, a flow of combustion air along the axial direction is formed at the center. Therefore, the cooling air flowing in from the cooling holes 2f is pressed against the inner wall of the combustor liner 2b by the flow of the combustion air. That is, even in the configuration in which the louver 2e is not provided, the cooling air can flow along the inner wall surface of the combustor liner 2b.

(3) In the above embodiment, the cooling structure is provided for the combustor liner 2b, but the present invention is not limited to this. The function is not limited as long as the structure has a high-temperature wall.

(4) Further, the combustor 2 may be of a can type or a cannula type and may include one or a plurality of cylindrical combustor liners 2b. In this case, a cooling structure is provided for each of the combustor liners 2b.

(5) Moreover, in the said embodiment, although air shall be used as a cooling fluid, this invention is not limited to this. For example, the cooling fluid can be changed according to the function of the structure, and may be an inert gas such as nitrogen, water in a liquid state, or the like.

(6) Moreover, in the said embodiment, although the diffusing member 2d shall be comprised with a sintered metal, this invention is not limited to this. The diffusing member 2d may be made of, for example, porous ceramics.

DESCRIPTION OF SYMBOLS 1 Compressor 1a Compressor blade 1b Compressor blade 1c Housing 2 Combustor 2a Fuel supply nozzle 2b Combustor liner 2c Swirler 2d Diffusion member 2e Louver 2f Cooling hole 3 Turbine shaft 3b Turbine blade 3c Turbine blade G Gas Turbine H1 Intake port H2 Exhaust port R1 Compressed air chamber R2 Combustion region

Claims (6)

A cooling structure for cooling the wall of the structure,
A cooling structure comprising a porous diffusion member that is provided on the wall and downstream of the cooling hole formed in the wall and through which a cooling fluid can pass.   The cooling structure according to claim 1, wherein the diffusion member is a sintered metal.   The cooling structure according to claim 1, further comprising a louver provided on the wall portion and guiding the cooling fluid along the wall surface.   The cooling structure according to claim 3, wherein the cooling hole is provided on a flow path of the cooling fluid formed by the louver and the wall surface. A combustor liner having a plurality of cooling holes formed in the circumferential direction;
A cooling structure according to any one of claims 1 to 4, and
The combustor, wherein the diffusion member is provided on an inner wall surface of the combustor liner.   The combustor according to claim 5, wherein the diffusion member is annularly shaped.

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