Combustor arrangement for a gas turbine

Patent metadata

Field	Value
Publication number	US-10352568-B2
Application number	US-201514925435-A
Country	US
Kind code	B2
Filing date	Oct 28, 2015
Priority date	Oct 31, 2014
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.

First claim

The invention claimed is:

1. A combustor arrangement for a gas turbine assembly, comprising:
a first burner;
a first combustion chamber;
a mixer for admixing a dilution gas to hot gases leaving the first combustion chamber during operation;
a second burner;
a second combustion chamber arranged sequentially in a fluid flow connection, wherein the first burner, the first combustion chamber, the mixer, the second burner and the second combustion chamber are arranged in a row to form a flow path extending between the first combustion chamber and the second burner;
a central lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer;
wherein the central lance body includes at least one air duct for providing air for the mixer between the first burner and the second burner, wherein the air is to be injected during operation into the combustor arrangement through air supply elements; and
wherein the central lance body comprises at least one fuel duct arranged within the central lance body and configured to provide fuel for the second burner, the at least one fuel duct having a curled duct on an input side, a longitudinal duct extending from the curled duct along a longitudinal axis of the central lance body to an L-shaped outlet, and wherein the L-shaped outlet is configured to provide the fuel to the second burner.

2. The combustor arrangement according to claim 1 , wherein the at least one air duct in the central lance body comprises a plurality of air ducts in the central lance body, and
wherein the plurality of air ducts are concentrically arranged annular-shaped passages along a longitudinal axis of the combustor arrangement and arranged adjacent to an outer housing surface of the central lance body.

3. The combustor arrangement according to claim 2 , wherein the annular-shaped passages have lengths to connect with at least two different air supply elements of the air supply elements along the central lance body.

4. The combustor arrangement according to claim 1 , wherein the air supply elements comprise:
annular passages, holes, slits or vents in a housing wall of the central lance body.

5. The combustor arrangement according to claim 1 ,
wherein a housing of the combustor arrangement partially encompasses the central lance body and is configured to be connected to a housing of a second burner reaction zone of the gas turbine,
wherein, in a connected position, a free end of the central lance body extends into the housing of the second burner reaction zone,
wherein the central lance body is surrounded by the flow path and is arranged inside a combustor housing,
wherein an air supply is provided in counter flow direction of the flow path outside of the second combustion chamber towards a cavity around first burner devices of the first burner to be introduced into the first burner devices or into the at least one air duct of the central lance body as well as into cavities of a double walled housing wall between the flow path and the air supply.

6. The combustor arrangement according to claim 1 , wherein the at least one fuel duct is two fuel ducts arranged within the central lance body, one of the two fuel ducts is configured to transport a first liquid fuel product and the other of the two fuel ducts is configured to transport a second gaseous fuel product to the burners.

7. The combustor arrangement according to claim 1 , wherein a housing of the combustor arrangement increases in a cross-section of a combustion cavity between a first burner stage towards a first burner reaction zone.

8. The combustor arrangement according to claim 1 , wherein a housing of the combustor arrangement increases in a cross-section of a combustion cavity between a second burner stage towards a second burner reaction zone of the combustor arrangement.

9. The combustor arrangement according to claim 1 , wherein the first burner comprises a plurality of first burners, each of the plurality of first burners comprises:
first fuel supply elements extending into a combustion cavity of the associated first burner, wherein the first fuel supply elements are connected with the at least one fuel duct.

10. The combustor arrangement according to claim 1 ,
wherein the first burner comprises between two and ten first burner devices in a first burner stage.

11. The combustor arrangement according to claim 1 , wherein the central lance body is removably mounted in the combustor arrangement.

12. The combustor arrangement according to claim 1 , wherein a cross section of the flow path increases in a counter flow direction such that the central lance body and fuel injectors extending from the central lance body are retractable in an axial direction out of the flow path.

13. The combustor arrangement according to claim 3 , wherein the air supply elements comprise:
annular passages, holes, slits or vents in a housing wall of the central lance body.

14. The combustor arrangement according to claim 13 ,
wherein a housing of the combustor arrangement partially encompasses the central lance body and is configured to be connected to a housing of a second burner reaction zone of the gas turbine,
wherein, in a connected position, a free end of the central lance body extends into the housing of the second burner reaction zone, wherein the central lance body is surrounded by the flow path and is arranged inside a combustor housing,
wherein an air supply is provided in a counter flow direction of the flow path outside of a combustor chamber towards a cavity around the first burner devices of the first burner to be introduced into the first burner devices or into the air ducts of the central lance body as well as into cavities of a double walled housing wall between the flow path and the air supply.

15. The combustor arrangement according to claim 13 , wherein the central lance body further comprises:
a first burner fuel duct for providing the fuel for the first burner.

16. The combustor arrangement according to claim 13 , wherein a housing of the combustor arrangement increases in a cross-section of a combustion cavity between a first burner stage towards a first burner reaction zone.

17. The combustor arrangement according to claim 13 , wherein a housing of the combustor arrangement increases in a cross-section of the combustion cavity between a second burner stage towards a second burner reaction zone of the combustor arrangement.

18. The combustor arrangement according to claim 13 , wherein the second burner comprises a plurality of second burners, each of the plurality of second burners comprises:
second fuel supply elements extending into a combustor cavity outside the central lance body, wherein the second fuel supply elements are connected with the at least one fuel duct, wherein the second fuel supply elements are lobed injectors.

19. The combustor arrangement according to claim 1 , wherein the second burner comprises a plurality of second burners, each of the plurality of second burners comprises:
second fuel supply elements extending into a combustor cavity outside the central lance body, wherein the second fuel supply elements are connected with the at least one fuel duct.

20. A combustor arrangement for a gas turbine assembly, comprising:
a first burner;
a first combustion chamber;
a mixer for admixing a dilution gas to hot gases leaving the first combustion chamber during operation;
a second burner;
a second combustion chamber arranged sequentially in a

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Eroglu Adnan
• Ciani Andrea
• Pennell Douglas Anthony

Classifications

• F23R3/36

  Supply of different fuels · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23R3/02 Primary

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · CPC title