Gas turbine combustor with top hat nozzle arrangements

Patent metadata

Field	Value
Publication number	US-9719419-B2
Application number	US-201213817384-A
Country	US
Kind code	B2
Filing date	Feb 28, 2012
Priority date	Mar 16, 2011
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

A gas turbine combustor includes: an external cylinder ( 31 ); an inner cylinder ( 32 ) provided inside the external cylinder ( 31 ) to form an air passage ( 30 ) between the external cylinder ( 31 ) and the inner cylinder ( 32 ); a pilot nozzle ( 35 ) provided in a center part of the inner cylinder ( 32 ) along a direction of a combustor axis (S); a plurality of main nozzles ( 36 ) provided on an inner peripheral surface of the inner cylinder ( 32 ) along a circumferential direction thereof so as to surround the pilot nozzle ( 35 ), the plurality of main nozzles ( 36 ) premixing fuel with combustion air introduced to the air passage ( 30 ) and ejecting the fuel into the inner cylinder ( 32 ); and a top hat nozzle ( 41 ) provided inside the air passage ( 30 ) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles ( 36 ).

First claim

The invention claimed is:

1. A gas turbine combustor comprising:
an external cylinder;
an inner cylinder provided inside the external cylinder to form an air passage between the external cylinder and the inner cylinder;
a pilot nozzle provided in a center part of the inner cylinder along a direction of a combustor axis;
a plurality of main nozzles provided on an inner peripheral surface of the inner cylinder along a circumferential direction thereof so as to surround the pilot nozzle, wherein the plurality of main nozzles are arranged to premix fuel with combustion air introduced to the air passage and eject the fuel into the inner cylinder; and
a plurality of top hat nozzles provided inside the air passage and including a plurality of fuel ejection ports, from which the fuel is ejected, across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles, wherein the plurality of top hat nozzles are aligned on an axial plane perpendicular to the direction of the combustor axis, and wherein, with respect to every pair of circumferentially adjacent fuel ejection ports of the plurality of fuel ejection ports, the circumferentially adjacent fuel ejection ports of the plurality of fuel ejection ports have different axial positions along the combustion axis direction from each other.

2. The gas turbine combustor according to claim 1 , wherein the axial positions of the plurality of fuel ejection ports are varied regularly along the circumferential direction.

3. The gas turbine combustor according to claim 2 , wherein the plurality of fuel ejection ports having different axial positions constitute a fuel ejection port group, and plural fuel ejection port groups are disposed in the combustor axis direction.

4. The gas turbine combustor according to claim 1 , wherein the axial positions of the plurality of fuel ejection ports are varied irregularly along the circumferential direction.

5. The gas turbine combustor according to claim 1 , wherein the plurality of the top hat nozzles are provided in the circumferential direction, the top hat nozzles respectively include the fuel ejection ports provided midway in the combustor axis direction to which the respective top hat nozzles extend, and the respective fuel ejection ports are disposed in a manner that the axial positions of the fuel ejection ports are varied regularly along the circumferential direction.

6. The gas turbine combustor according to claim 5 , wherein the top hat nozzles respectively have a plurality of the fuel ejection ports disposed in the combustor axis direction.

7. The gas turbine combustor according to claim 1 , wherein the plurality of the top hat nozzles are provided in the circumferential direction, the top hat nozzles respectively include the fuel ejection ports provided midway in the combustor axis direction to which the respective top hat nozzles extend, and the respective fuel ejection ports are disposed in a manner that the axial positions of the fuel ejection ports are varied irregularly along the circumferential direction.

8. The gas turbine combustor according to claim 1 , wherein the plurality of the top hat nozzles are provided in the circumferential direction, the top hat nozzles respectively have a vane shape for rectifying the combustion air introduced to the air passage, and the top hat nozzles respectively include the fuel ejection ports, and the respective fuel ejection ports are disposed in a manner that the axial positions of the fuel ejection ports are varied regularly along the circumferential direction.

9. The gas turbine combustor according to claim 8 , wherein the top hat nozzles are respectively provided with a plurality of the fuel ejection ports disposed in the combustor axis direction.

10. The gas turbine combustor according to claim 1 , wherein the plurality of the top hat nozzles are provided in the circumferential direction, the top hat nozzles respectively have a vane shape for rectifying the combustion air introduced to the air passage, and the top hat nozzles respectively include the fuel ejection ports, and the respective fuel ejection ports are disposed in a manner that the axial positions of the fuel ejection ports are varied irregularly along the circumferential direction.

11. A gas turbine comprising the gas turbine combustor according to claim 1 .

Assignees

• Sometani Satoshi
• Takiguchi Satoshi
• Mandai Shigemi
• Mitsubishi Heavy Ind Ltd

Inventors

• Sometani Satoshi
• Takiguchi Satoshi
• Mandai Shigemi

Classifications

• F23R3/286

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

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F23R3/54

  Reverse-flow combustion chambers · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title