Combustion burner, combustor, and gas turbine having a swirl vane with opposite directed surfaces

Patent metadata

Field	Value
Publication number	US-10240791-B2
Application number	US-201514897814-A
Country	US
Kind code	B2
Filing date	Jan 23, 2015
Priority date	Sep 19, 2014
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

First claim

The invention claimed is:

1. A combustion burner comprising:
a nozzle; and
a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle around the nozzle,
wherein the swirl vane includes
a tip portion for swirling gas in a swirl direction, the gas flowing through a radially-outer region of the axial flow path, and
a root portion disposed on an inner side in a radial direction of the nozzle as seen from the tip portion, the root portion having a cutout on a side of a trailing edge,

wherein the radially-outer region and a radially-inner region of the axial flow path communicate with each other without being partitioned, at least in a range in the axial direction in which the swirl vane is disposed,
wherein the swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge,
wherein the trailing edge of the root portion of the swirl vane is formed by a downstream edge of the curved surface in the axial direction, the trailing edge of the root portion being disposed on an upstream side in the axial direction as compared to the trailing edge of the tip portion,
wherein the pressure surface of the swirl vane at the tip portion has a curved surface curving in the swirl direction toward the trailing edge, and
wherein the pressure surface of the swirl vane has a stepped portion between the curved surface of the tip portion and the curved surface of the root portion.

2. The combustion burner according to claim 1 ,
wherein the trailing edge of the root portion of the swirl vane is disposed on an upstream side in the swirl direction, as compared to the trailing edge of the tip portion.

3. The combustion burner according to claim 2 ,
wherein the trailing edge of the root portion of the swirl vane is disposed on a position same as that of a leading edge of the root portion, in a circumferential direction of the nozzle.

4. The combustion burner according to claim 1 ,
wherein the airfoil of the root portion of the swirl vane has a line-symmetric shape with respect to a straight line parallel to the axial direction and passing through the trailing edge, at least on the side of the trailing edge.

5. The combustion burner according to claim 2 ,
wherein the trailing edge of the root portion of the swirl vane is disposed on a side opposite to the trailing edge of the tip portion across a straight line parallel to the axial direction and passing through the leading edge, in the circumferential direction of the nozzle.

6. The combustion burner according to claim 1 ,
wherein the curved surface at the root portion is configured to swirl gas in a direction opposite to the swirl direction, the gas flowing through the radially-inner region of the axial flow path.

7. The combustion burner according to claim 1 ,
wherein a bisector of an angle formed by a tangent of the pressure surface passing through the trailing edge of the root portion and a tangent of a suction surface passing through the trailing edge of the root portion is oblique to the axial direction in a direction opposite to the swirl direction, at a downstream side of the trailing edge.

8. The combustion burner according to claim 1 ,
wherein the leading edge of the swirl vane is oblique to the radial direction toward an upstream side in the axial direction as the leading edge gets closer to an outer side in the radial direction of the nozzle, at least on a side of the tip portion.

9. The combustion burner according to claim 1 ,
wherein the tip portion includes a cutout-space forming surface disposed on a radially-outer side of a cutout space formed by the cutout, the cutout-space forming surface facing the cutout space, in a downstream region of the tip portion, and
wherein the cutout-space forming surface has a shape such that a width of the cutout space in the radial direction increases toward a downstream side.

10. The combustion burner according to claim 9 ,
wherein the cutout-space forming surface is a flat surface extending linearly and oblique to the axial direction so that the width of the cutout space in the radial direction increases toward the downstream side.

11. A combustor comprising:
the combustion burner according to claim 1 , and
a combustor liner for forming a flow path for guiding combustion gas from the combustion burner.

12. A gas turbine comprising:
a compressor for generating compressed air;
the combustor according to claim 11 configured to combust fuel with the compressed air from the compressor to generate combustion gas; and
a turbine configured to be driven by the combustion gas from the combustor.

13. A combustion burner comprising:
a nozzle; and
a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle around the nozzle, wherein the swirl vane includes
a tip portion for swirling gas in a swirl direction, the gas flowing through a radially-outer region of the axial flow path, and
a root portion disposed on an inner side in a radial direction of the nozzle as seen from the tip portion, the root portion having a cutout on a side of a trailing edge,

wherein the radially-outer region and a radially-inner region of the axial flow path communicate with each other without being partitioned, at least in a range in the axial direction in which the swirl vane is disposed,
wherein the swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge,
wherein the pressure surface of the swirl vane at the tip portion has a curved surface curving in the swirl direction toward the trailing edge,
wherein the pressure surface of the swirl vane has a stepped portion between the curved surface of the tip portion and the curved surface of the root portion,
wherein an airfoil of the root portion has a shape same as that of an airfoil of the tip portion in an upstream region, and has a shape such that a portion corresponding to the cutout is cut out from the airfoil of the tip portion in the downstream region, and
wherein the trailing edge of the root portion of the swirl vane is formed by a downstream edge of the pressure surface of the root portion including the curved surface so as to be disposed on a suction surface of the airfoil of the root portion having the same shape as the tip portion.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Nagai Naonori
• Tada Katsuyoshi
• Inoue Kei
• Saito Keijiro

Classifications

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23C2900/07001

  Air swirling vanes incorporating fuel injectors · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title