Sequential combustion with dilution gas mixer

Patent metadata

Field	Value
Publication number	US-10330319-B2
Application number	US-201514693045-A
Country	US
Kind code	B2
Filing date	Apr 22, 2015
Priority date	Oct 24, 2012
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

The invention refers to a sequential combustor arrangement including 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. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

First claim

The invention claimed is:

1. A sequential combustor arrangement comprising:
a first burner;
a first combustion chamber;
a mixer for admixing a dilution gas to cool hot gases leaving the first combustion chamber during operation;
a second burner;
a second combustion chamber arranged sequentially in a fluid flow connection; and
a connection duct configured for cooling a liner of the combustor arrangement with dilution gas from a compressor, wherein the connection duct is inside a compressed air plenum formed by an outer casing of the sequential combustor arrangement,
wherein the mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber and the second burner, the mixer being formed as a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner,
wherein the mixer includes a plurality of injection pipes pointing inwards from side walls of the mixer for injecting the dilution gas from the connection duct to cool the hot gases leaving the first combustion chamber, and
wherein at least one of the plurality of injection pipes includes a pipe wall having cooling holes on a downstream side and a thermal barrier coating on an upstream side.

2. The combustor arrangement according to claim 1 , comprising:
first injection pipes of the plurality of injection pipes, the first injection pipes having a first intrusion depth into the hot gas flow path normal to the side wall of the mixer; and
second injection pipes of the plurality of injection pipes, the second injection pipes having a second intrusion depth into the hot gas flow path normal to the side wall of the mixer, which is smaller than the first intrusion depth.

3. The combustor arrangement according to claim 1 , wherein a ratio of a first intrusion depth of a first injection pipe of the plurality of injection pipes to a second intrusion depth of a second injection pipe of the plurality of injection pipes is at least greater than 2.

4. The combustor arrangement according to claim 1 , wherein a ratio of equivalent diameter of a cross section of the hot gas flow path at a location of first injection pipes of the plurality of injection pipes in the mixer to a length of the first injection pipes is in a range of at least 2.5 to 8.

5. The combustor arrangement according to claim 1 , wherein a ratio of a length of a second injection pipe of the plurality of injection pipes to a diameter of the second injection pipe is smaller than 1/4.

6. The combustor arrangement according to claim 1 , wherein second injection pipes of the plurality of injection pipes or injection holes are arranged downstream of first injection pipes of the plurality of injection pipes to compensate for a wake of the first injection pipes and/or in that the second injection pipes or injection holes are arranged upstream of the first injection pipes to reduce axial flow velocities of the hot gas flow before the first injection pipes.

7. The combustor arrangement according to claim 1 , wherein a distance in flow direction between at least one first injection pipe and at least one second injection pipe is less than three times a diameter of the at least one first injection pipe.

8. The combustor arrangement according to claim 1 , wherein first or second injection pipes of the plurality of injection pipes of one length are arranged circumferentially distributed along the side wall of the mixer in one plane normal to a main flow direction of the hot gases flowing through the mixer or the first or second injection pipes are arranged circumferentially distributed along the side wall of the mixer and staggered relative to a plane normal to the main flow direction of the hot gases flowing through the mixer to reduce flow blockage due to the first or second injection pipes wherein the stagger is less than half a diameter of the first or second injection pipe.

9. The combustor arrangement according to claim 1 , comprising:
cooling ribs and/or a pin field arranged on an inner surface of at least one injection pipe of the plurality of injection pipes.

10. The combustor arrangement according to claim 1 , wherein the thermal barrier coating is applied on an outer surface of the at least one of the plurality of injection pipes and the cooling holes are diffusion cooling holes.

11. The combustor arrangement according to claim 1 , wherein the mixer comprises a diffusor section upstream of the dilution air admixing to reduce a flow velocity of the hot gases, and/or in that the mixer comprises a diffusor section in a region of the dilution air admixing to increase a flow area with a same ratio as volume flow increases due to the admixing of the dilution air to keep an average axial flow velocity constant and/or to limit an increase in the average axial velocity to plus 20% of the axial velocity upstream of an admixing location.

12. The combustor arrangement according to claim 1 , wherein at least one injection pipe of the plurality of injection pipes is inclined at an angle of less than 90° relative to a flow direction of the hot gases such that the dilution gas leaving the at least one injection pipe has a flow component in a direction of the hot gas flow at the location of injection.

13. A method for operating a gas turbine with at least a compressor, a combustor arrangement 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 connected to an outlet of the mixer at a downstream end for connection to the second burner, a second combustion chamber arranged sequentially in a fluid flow connection, a connection duct configured for cooling a liner of the combustor arrangement with dilution gas from a compressor, and a turbine, wherein the connection duct is inside a compressed air plenum formed by an outer casing of the combustor arrangement, wherein the mixer includes a plurality of injection pipes pointing inwards from the side walls of a duct, and wherein at least one of the plurality of injection pipes includes a pipe wall having cooling holes, the method comprising:
guiding, via the mixer, combustion gases in a hot gas flow path extending between the first combustion chamber and the second combustion chamber;
injecting the dilution gas from the connection duct via the plurality of injection pipes to cool hot flue gases leaving the first combustion chamber, wherein the dilution gas is admixed into different regions of the cross section of the mixer; and
transferring heat from the pipe wall via a thermal barrier coating applied on an upstream side of the pipe wall and reducing a pressure drop in a hot gas flow via the cooling holes provided on a downstream side of the pipe wall.

14. The method as claimed in claim 13 , comprising:
injecting dilution gas through injection holes and/or second injection pipes of the plurality of injection pipes and first injection pipes of the plurality of injection pipes in order to introduce the dilution gas into different regions of the cross section of the mixer.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Duesing Michael
• Tay Wo Chong Hilares Luis
• Bothien Mirko Ruben
• Hellat Jaan
• Schuermans Bruno

Classifications

• F23R3/346

  for staged combustion · CPC title

• F02C6/02

  Plural gas-turbine plants having a common power output · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/964

  counteracting thermoacoustic noise · CPC title