Sequential combustion arrangement with cooling gas for dilution

Patent metadata

Field	Value
Publication number	US-10677453-B2
Application number	US-201615234605-A
Country	US
Kind code	B2
Filing date	Aug 11, 2016
Priority date	Aug 12, 2015
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A gas turbine with a sequential combustor arrangement as disclosed includes a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, a second burner for admixing a second fuel and a second combustion chamber. To assure a temperature profile after the dilution gas admixer and to increase the gas turbine's power and efficiency a vane and/or blade of the turbine has a closed loop cooling. The outlet of the closed loop cooling is connected to the dilution gas admixer for admixing the heated cooling gas leaving the vane and/or blade into the first combustor combustion products.

First claim

The invention claimed is:

1. A gas turbine comprising:
a compressor,
a turbine, and
a sequential combustor arrangement comprising:
a first combustor with a first burner for admitting a first fuel into a first combustion chamber for burning the first fuel to form first combustor combustion products;
a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber;
a second burner for admixing a second fuel in a second combustion chamber, wherein the first combustor, the dilution gas admixer, the second burner and the second combustion chamber are arranged sequentially and are in a fluid flow connection;
a vane and/or blade of the turbine having a cooling loop which is connected to a compressor plenum for feeding compressed cooling fluid into the vane and/or blade to cool the vane and/or blade, the cooling loop of the vane and/or blade configured to internally cool the vane and/or blade without being discharged from the vane and/or blade into hot gas flowing around an exterior of the vane and/or blade, the cooling loop having an outlet connected to the dilution gas admixer, the outlet of the cooling loop being positioned and configured to pass the compressed cooling fluid that has flowed within the vane and/or blade of the turbine to the dilution gas admixer so that the compressed cooling fluid that is heated via flowing within the vane and/or blade to cool the vane and/or blade passes to the dilution gas admixer to he injected into the first combustion products as the dilution gas so that the compressed cooling fluid that was heated from passing within the vane and/or blade to cool the vane and/or blade is subsequently admixed with the first combustor combustion products via the dilution gas admixer to facilitate generation of a homogenous temperature profile for the admixed first combustion products and dilution gas to be fed to the second burner to reduce NOx emission values;
the dilution gas admixer positioned upsteam of the second burner, with respect to a flow direction of the first combustor combustion products, and configured to receive the compressed cooling fluid from the outlet of the cooling loop and inject the dilution gas into the first combustor combustion products such that the compressed cooling fluid that was heated from passing within the vane and/or blade to cool the vane and or blade is admixed with the first combustor combustion products via, the dilution gas admixer to generate the homogenous temperature profile for the admixed first combustor combustion products and dilution gas to reduce NOx emission values for feeding the admixed first combustion products and dilution gas to the second burner; and
an additional cooling loop to cool an additional vane and/or blade positioned upstream of the vane and/or blade, with respect to the flow direction of the first combustor combustion products, the additional cooling loop being connected to the compressor plenum to receive the compressed cooling fluid, being open to discharge from the additional vane and/or blade, and being connected to the gas admixer to provide additional compressed heated fluid to the first combustion products.

2. The gas turbine as claimed in claim 1 , wherein the cooling loop has a cooling gas feed connecting the compressor plenum to the cooling loop.

3. The gas turbine as claimed in claim 2 , wherein the cooling gas feed is arranged between a rotor and the sequential combustor arrangement.

4. The gas turbine as claimed in claim 2 , wherein the cooling gas feed is arranged between a combustor casing and the sequential combustor arrangement.

5. The gas turbine as claimed in claim 1 , comprising:
a cooling channel for cooling at least one of a first combustion liner of the first combustor, a second combustor liner of the second combustor, a wall of the second burner, a mixing section, and the dilution gas admixer.

6. The gas turbine as claimed in claim 1 , comprising: an ejector pump interposed between the outlet of the cooling loop and the dilution gas admixer.

7. The gas turbine as claimed in claim 1 , comprising: at least one feed to the dilution gas admixer directly connected to the compressor plenum for additionally admixing compressor exit gas into the first combustor combustion products.

8. A method for operating a gas turbine having a compressor, a turbine and a sequential combustor arrangement with a first combustor having a first burner and a first combustion chamber, a dilution gas admixer, a second burner and a second combustion chamber, wherein the first combustor, the dilution gas admixer, the second burner, and second combustion chamber are arranged sequentially in a fluid now connection, the method comprising: compressing inlet gas in the compressor;
burning a mixture in the first combustion chamber to obtain first combustor combustion products;
passing compressed gas through a cooling loop of a vane and/or blade of the turbine so that the compressed gas is passed within the vane and/or blade to internally cool the vane and/or blade without the compressed gas passing through the vane and/or blade being discharged into hot gas flowing around an exterior of the vane and/or blade;
feeding the compressed gas from the cooling loop of the vane and/or blade to the dilution gas admixer without recompression of the compressed gas after the compressed gas is passed through the cooling loop of the vane and/or blade to internally cool the vane and/or blade;
generating a homogenous temperature profile of the first combustor combustion products and dilution gas to reduce NOx emission values by admixing dilution gas to the first combustor combustion products leaving the first combustion chamber in the dilution gas admixer for feeding the dilution gas admixed with the first combustor combustion products to the second burner to generate the homogenous temperature profile for the first combustor combustion products and dilution gas to reduce the NOx emission values, the dilution gas including the compressed gas fed to the dilution gas admixer from the cooling loop of the vane and/or blade to facilitate generation of the homogenous temperature profile for the admixed first combustor combustion products and dilution gas to reduce the NOx emission values;
feeding the admixed dilution gas and the first combustor products having the homogenous temperature profile to the second burner;
passing additional compressed gas through an additional cooling loop to cool an additional vane and/or blade positioned upstream of the vane and/or blade, with respect to a flow direction of the first combustor combustion products, the additional cooling loop being open to discharge from the additional vane and/or blade; and
feeding the additional compressed gas from the additional cooling loop to the gas admixer to provide additional compressed heated fluid to the first combustor combustion products.

9. The method for operating a gas turbine according to claim 8 , comprising:
feeding the compressed gas from a compressor plenum into the cooling loop of the vane and/or blade.

10. The method for operating a gas turbine according to claim 8 , comprising:
feeding the compressed gas from a cooling gas feed to the cooling loop of the vane and/or blade, the cooling gas feed being arranged between a rotor and the sequential combustor arrangement.

11. The method for operating a gas turbine according to claim 8 , comprising: feeding the compressed gas to the cooling loop from a cooling gas feed arranged between a combustor casing and the sequential combustor arrangement.

12. The method for operating a gas turbine as claimed in claim 8 , the wherein the

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Reiter Wilhelm
• Hoffmann Jürgen Gerhard

Classifications

• F23C6/047 Primary

  with fuel supply in stages · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F01D5/187

  Convection cooling · CPC title

• F23R3/02

  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

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title