JP3001224U - Combustor for gas turbine - Google Patents

Abstract

(57) [Summary] [Object] To provide a combustor for a gas turbine having a simple structure and a scroll structure in which combustion air is uniformly supplied to a combustion chamber while minimizing pressure loss. . In a gas turbine combustor C having a scroll structure 2, a rectifying means 3 having a small pressure loss, for example, a flow, is formed near an open end of a combustion air flow path formed by the scroll structure 2 to a combustion chamber 4. The stationary vanes 3 are provided along the side. Therefore, it is possible to uniformly supply the air to the combustion chamber 4 while suppressing the pressure loss to the extent that there is no practical problem.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention relates to a gas turbine combustor having a scroll structure. More specifically, it relates to a gas turbine combustor having a scroll structure capable of uniformly supplying air to a combustion chamber while minimizing pressure loss.

[0002]

[Prior art]

 In medium- and small-sized gas turbines, combustion air is compressed by a radial turbine and discharged inside the main housing, and then is gathered by an air flow path that has a scroll structure with its ends open toward the combustion chamber. It is guided to the combustion chamber. Due to the complicated flow passage shape of this scroll structure, the combustion air flows into the combustion chamber with a non-uniform flow velocity distribution.

Therefore, there is a problem that combustion becomes unbalanced and a local high temperature part is generated on the wall surface of the combustion chamber and the turbine stationary blade, and they may be burnt out. In addition, there is a problem that it is difficult to reduce NOx when a high temperature part is locally generated.

In order to eliminate the non-uniform flow velocity distribution of the combustion air in the gas turbine combustor having such a scroll structure, swirl vanes are provided at the inlet of the combustion chamber to rectify the flow of the combustion air. A structure has been proposed in which combustion air is uniformly supplied to the combustion chamber.

However, in such a structure, there is a problem that the pressure loss due to the swirl vanes becomes large, which causes a reduction in the efficiency of the gas turbine.

Further, in Japanese Utility Model Laid-Open No. 60-18597, at a confluence portion of a pair of left and right gas passages of a scroll body on a downstream side of a gas suction port, a partition member integrated with the scroll body is used for partitioning and separating However, it is proposed that each of these flow paths be connected to a conduit to a gas turbine.

Certainly, according to such a configuration, the combustion air supplied to the combustion chamber is certainly balanced to some extent. However, with such a configuration, the structure of the scroll having a complicated shape becomes more complicated, which causes a problem of increasing the manufacturing cost.

[0008]

[Problems to be solved by the device]

 The present invention has been made in view of the above problems of the prior art, and has a scroll structure having a simple structure and capable of uniformly supplying combustion air to a combustion chamber while minimizing pressure loss. The purpose is to provide a combustor for the gas turbine.

[0009]

[Means for Solving the Problems]

 According to the present invention, in a gas turbine combustor having a scroll structure, a rectifying means having a small pressure loss is provided near an open end of a combustion air passage formed by the scroll structure to a combustion chamber. And

Here, as the rectifying means, the vanes along the flow direction provided near the open end of the combustion air flow path to the combustion chamber and the flow provided near the open end to the combustion chamber It is considered to be a row of stationary vanes along the direction.

In the present invention, it is preferable that the stationary vanes of the stationary vane row have an isosceles triangle whose base is arcuate and whose top is directed to the upstream side.

[0012]

[Action]

 The gas turbine combustor of the present invention is provided with a rectifying means with a small pressure loss near the open end to the combustion chamber of the combustion air flow path formed by the scroll structure as described above, and therefore the The air flow discharged from the end of the configured air flow path to the outer wall of the combustion chamber is rectified without causing a pressure loss that poses a practical problem. As a result, combustion air can be uniformly supplied to the combustion chamber while minimizing pressure loss.

[0013]

【Example】

 Hereinafter, the present invention will be described based on embodiments with reference to the accompanying drawings, but the present invention is not limited to such embodiments.

Embodiment 1 FIGS. 1 to 4 show a gas turbine combustor C according to Embodiment 1 of the present invention. In Embodiment 1, the present invention is applied to a gas turbine combustion apparatus having a single fuel injection nozzle 5. It is applied to the container C. That is, the rectifying means 3 with a small pressure loss is provided from the lower surface to the upper surface of the air flow path near the open end of the air flow path of the scroll structure 2 to the combustion chamber 4. As the rectifying means 3 with a small pressure loss, for example, as shown in the cross section of FIG. 4, a vane 3 having an isosceles triangle whose base is arcuate is directed toward the upstream side of the top of the triangle. That is, some are arranged along the flow. However, the rectification means 3 having a small pressure loss is not limited to this, and for example, the rectifying means 3 in which the stationary vanes are slim and arranged in parallel may be used.

The arrow in FIG. 1 indicates the direction of air flow, and 1 indicates the main housing.

Embodiment 2 FIGS. 5 to 8 show a combustor C for a gas turbine according to Embodiment 2 of the present invention. Embodiment 2 is an embodiment of the present invention for a gas turbine having a plurality of fuel injection nozzles 5, 5. It is applied to the combustor C. Other than being applied to the gas turbine combustor C having a plurality of fuel injection nozzles 5 and 5, it is the same as in the first embodiment, so a detailed description thereof is omitted.

Experimental Example and Comparative Experimental Example The gas turbine combustor C of Example 1 was used to measure the flow direction and velocity at the position shown in FIG. 9 (Experimental Example). The result is shown in FIG.

For comparison, a gas turbine combustor configured in the same manner as in Example 1 was used, except that the rectifying means 3 having a small pressure loss was not provided, and the flow direction and velocity were the same as in the experimental example. Was measured (comparative experiment example). The result is shown in FIG. 10 and 11, the direction of the arrow indicates the flow direction, and the length thereof indicates the magnitude of the flow velocity.

From FIGS. 10 and 11, it can be seen that the flow is uniform in the experimental example and non-uniform in the comparative experimental example. Therefore, in the experimental example, the rectification operation by the stationary blade is recognized.

[0020]

[Effect of device]

 As described above, according to the present invention, it is possible to uniformly supply air to the combustion chamber while suppressing the pressure loss of the combustion air to the extent that there is no practical problem with a simple configuration. can get. Therefore, stable combustion is achieved, a local temperature rise is avoided, and the excellent effect that NOX can also be reduced is obtained.

[Brief description of drawings]

FIG. 1 is an overall perspective view of a first embodiment of the present invention.

FIG. 2 is a vertical cross-sectional view of FIG.

3 is an axial cross-sectional view of FIG.

FIG. 4 is a horizontal sectional view of FIG.

FIG. 5 is an overall perspective view of a second embodiment of the present invention.

6 is a lateral cross-sectional view of FIG.

7 is a vertical cross-sectional view of FIG.

FIG. 8 is a horizontal sectional view of FIG.

FIG. 9 is an explanatory diagram showing measurement positions in an experimental example and a comparative experimental example.

FIG. 10 is a graph showing measurement results in an experimental example.

FIG. 11 is a graph showing measurement results in a comparative experiment example.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Main housing 2 Scroll (scroll structure) 3 Low pressure loss rectifying means (stator vanes) 4 Combustion chamber 5 Fuel injection nozzle C Gas turbine combustor

Front page continued (72) Shinichi Oga 1-1 Kawasaki-cho, Akashi-shi, Kawasaki Heavy Industries Ltd. Akashi Plant (72) Inventor Shinichi Kajita 1-1, Kawasaki-cho, Akashi-shi Akashi-shi Stock Corporation Akashi Inside the factory (72) Takeyoshi Kimura 1-1 Kawasaki-cho, Akashi City Kawasaki Heavy Industries Ltd. Akashi Factory

Claims (5)

[Scope of utility model registration request] 1. A gas turbine combustor having a scroll structure, characterized in that a rectifying means having a small pressure loss is provided near an open end of a combustion air flow path formed by the scroll structure to a combustion chamber. Combustor for gas turbine. 2. The gas turbine according to claim 1, wherein the rectifying means is a vane provided near the open end of the combustion air flow path to the combustion chamber and extending along the flow direction. Combustor. 3. The stator vane along the flow direction is an isosceles triangle whose base is arcuate and whose top is directed toward the upstream side. Combustor for gas turbine. 4. The gas turbine according to claim 1, wherein the rectifying means is a row of vanes along a flow direction, which is provided near an open end of the combustion air flow path to a combustion chamber. Combustor. 5. The gas turbine according to claim 4, wherein the vane of the vane row is an isosceles triangle whose base is arcuate and whose top is directed upstream. Combustor.