Combustor arrangement for a gas turbine

Patent metadata

Field	Value
Publication number	US-2016123597-A1
Application number	US-201514925527-A
Country	US
Kind code	A1
Filing date	Oct 28, 2015
Priority date	Oct 31, 2014
Publication date	May 5, 2016
Grant date	—

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 combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

First claim

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 the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection, wherein the first burner, the first combustion chamber, the mixer for admixing the dilution gas before 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, wherein the combustor arrangement includes a central lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and optionally into the second burner, wherein the central lance body includes at least one fuel duct for providing fuel for the first burner and/or for the second burner.

2 . The combustor arrangement according to claim 1 , wherein at least one of the fuel ducts are double line ducts arranged within the lance body to transport a first liquid fuel product and a second gaseous fuel product to the burners.

3 . The combustor arrangement according to claim 1 , wherein the central lance body is surrounded by the flow path and is arranged inside a combustor housing.

4 . The combustor arrangement according to claim 3 , wherein the central lance body comprises:
at least one air duct for providing air for at least one mixer between the associated first burner and the associated second burner, wherein the air is to be injected during operation into the combustor through air supply elements.

5 . The combustor arrangement according to claim 4 , wherein the air supply elements comprise holes, slits or vents in the housing wall of the lance body and/or in the housing wall of the opposite combustor housing.

6 . The combustor arrangement according to claim 3 , wherein the housing of the combustor arrangement increases the cross-section of the combustion cavity between the first burner stage towards the first burner reaction zone.

7 . The combustor arrangement according to claim 3 , wherein the housing of the combustor arrangement increases the cross-section of the combustion cavity between the second burner stage towards a second burner reaction zone of the combustor arrangement.

8 . The combustor arrangement according to claim 3 , wherein the housing of the combustor arrangement partially encompasses the lance body and is configured to be connected to a housing of the second burner reaction zone of the turbine, wherein, in the connected position, the free end of the lance body extends into the housing of the second burner reaction zone.

9 . The combustor arrangement according to claim 3 , wherein the housing of the combustor arrangement comprises:
an air duct cavity arranged to provide air for at least one air injection stage between the associated first burner and the associated second burner, wherein the air is to be injected into the combustor cavity through air supply elements which are annular passages in the housing wall.

10 . The combustor arrangement according to claim 1 , wherein at least one air duct of the central lance body is configured for providing air for a mixing stage between the second burner and the associated second burner reaction zone, wherein the air is to be injected into the combustor through air supply elements, which are configured as annular passages, holes, slits or vents in the housing wall of the end of the lance body and/or in the housing wall of the opposite combustor housing.

11 . The combustor arrangement according to claim 1 , wherein each second burner comprises:
second fuel supply elements extending into the combustor cavity outside the trunk of the lance body, wherein the second fuel supply elements are connected with the fuel ducts, wherein the second fuel supply elements are configured as lobed or micro VG injectors.

12 . The combustor arrangement according to claim 1 , wherein each first burner comprises:
first fuel supply elements extending into the combustion cavity of the associated first burner, wherein the first fuel supply elements are connected with the fuel ducts, wherein the first fuel supply elements are axial swirler injectors, flame sheet injectors, EV or AEV burners.

13 . The combustor arrangement according to claim 1 , comprising:
between two and ten first burner devices in the first burner stage.

14 . The combustor arrangement according to claim 1 , wherein the central lance body is removably mounted in the combustor arrangement, and configured for an optional axial removal along a longitudinal axis of the combustor arrangement.

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

16 . The combustor arrangement according to claim 5 , wherein the housing of the combustor arrangement increases the cross-section of the combustion cavity between the first burner stage towards the first burner reaction zone.

17 . The combustor arrangement according to claim 5 , wherein the housing of the combustor arrangement increases the cross-section of the combustion cavity between the second burner stage towards a second burner reaction zone of the combustor arrangement.

18 . The combustor arrangement according to claim 16 , wherein the housing of the combustor arrangement partially encompasses the lance body and is configured to be connected to a housing of the second burner reaction zone of the turbine, wherein, in the connected position, the free end of the lance body extends into the housing of the second burner reaction zone.

19 . The combustor arrangement according to claim 18 , wherein the housing of the combustor arrangement comprises:
an air duct cavity arranged to provide air for at least one air injection stage between the associated first burner and the associated second burner, wherein the air is to be injected into the combustor cavity through air supply elements, which are annular passages in the housing wall.

20 . The combustor arrangement according to claim 19 , wherein at least one air duct of the central lance body is configured for providing air for a mixing stage between the second burner and the associated second burner reaction zone, wherein the air is to be injected into the combustor through air supply elements, which are configured as annular passages, holes, slits or vents in the housing wall of the end of the lance body and/or in the housing wall of the opposite combustor housing.

Assignees

• Alstom Technology Ltd

Inventors

• Pennell Douglas Anthony
• Benz Urs
• Eroglu Adnan
• Freitag Ewald
• Bothien Mirko Ruben
• Ciani Andrea

Classifications

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F23C2900/07021

  Details of lances · CPC title

• F23C6/045

  with staged combustion in a single enclosure · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F23R3/283

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