Gas turbine assembly and corresponding operating method

Patent metadata

Field	Value
Publication number	US-10774740-B2
Application number	US-201314048878-A
Country	US
Kind code	B2
Filing date	Oct 8, 2013
Priority date	Apr 8, 2011
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

First claim

The invention claimed is:

1. A gas turbine assembly, comprising:
at least one compressor;
a plurality of combustion chamber elements accommodated in a housing of the gas turbine assembly, each of the plurality of combustion chamber elements having a first burner group, the first burner group comprising a plurality of first burners, and a transition duct having at least one second burner, the at least one second burner being a Sequential EnVironmental (SEV) burner arranged on a contraction of the transition duct, the transition duct and the at least one second burner being downstream of the first burner group without an interposed turbine arranged between the first burner group and the at least one second burner, and wherein the transition duct is configured to deliver a combustion gas from the first reaction zone to the at least one second burner at 900° C. to 1100° C. for autoignition of a fuel from the at least one second burner;
at least one turbine downstream of the plurality of combustion chamber elements;
at least one rotor;
wherein the plurality of combustion chamber elements are arranged in a form of a ring around the at least one rotor of the gas turbine assembly, each of the plurality of combustion chamber elements extending between the at least one compressor and the at least one turbine, each of the plurality of combustion chamber elements having a tubular or shape-changing cross section and extending at a radial distance from the at least one rotor of the gas turbine assembly, and includes the transition duct arranged downstream of a first reaction zone belonging to the first burner group, the first reaction zone having a round cross sectional shape;
wherein the first burner group, the at least one second burner, the first reaction zone, a second reaction zone belonging to the at least one second burner, and the transition duct are each located within each of the plurality of combustion chamber elements;
wherein the plurality of combustion chamber elements are configured during operation to maintain with respect to one another either an autonomous or quasi-autonomous sequential combustion;
wherein each of the transition ducts has a cross sectional shape, which is round, oval, or elliptical, and wherein the cross sectional shape of the transition duct contracts from the cross sectional shape of the first reaction zone and expands to a rectangular cross sectional shape; and
wherein each of the second reaction zones has the rectangular cross sectional shape.

2. The gas turbine assembly as claimed in claim 1 , wherein the transition duct is designed as a heat exchanger.

3. The gas turbine assembly as claimed in claim 1 , wherein each of the plurality of first burners is a premix burner.

4. The gas turbine assembly as claimed in claim 3 , wherein the premix burner is operated at least with an H 2 -rich fuel.

5. The gas turbine assembly as claimed in claim 1 wherein rotating parts of the at least one compressor and the at least one turbine are arranged on a common rotor.

6. The gas turbine assembly as claimed in claim 1 wherein the gas turbine assembly is an integral part of a gas/steam combined-cycle power plant.

7. The gas turbine assembly as claimed in claim 1 , wherein the plurality of first burners are one or more of the following:
premix burners, diffusion burners, and hybrid burners.

8. The gas turbine assembly as claimed in claim 1 , wherein each of the plurality of combustion chamber are individually arranged around the at least one rotor, and wherein the at least one rotor is a common rotor.

9. The gas turbine assembly as claimed in claim 1 , wherein the at one second burner comprises a plurality of second burners.

10. The gas turbine assembly as claimed in claim 1 , wherein a part of a compressor air and/or a steam quantity and/or another gas is introduced at the transition duct into the combustion gases originating from the first burner group.

11. A method for operating a gas turbine assembly comprising at least one compressor, a plurality of combustion chamber elements accommodated in a housing of the gas turbine assembly, each of the plurality of combustion chamber elements having a first burner group, the first burner group comprising a plurality of first burners, and a transition duct having at least one second burner, the at least one second burner being a Sequential EnVironmental (SEV) burner arranged on a contraction of the transition duct, the transition duct and the at least one second burner being downstream of the first burner group without an interposed turbine arranged between the first burner group and the at least one second burner, at least one turbine downstream of the plurality of combustion chamber elements, at least one rotor, and wherein the plurality of combustion chamber elements are arranged in a form of a ring around the at least one rotor of the gas turbine assembly, each of the combustion chamber elements extending between the at least one compressor and the at least one turbine, each of the plurality of combustion chamber elements having a tubular cross section and extending at a radial distance from the at least one rotor of the gas turbine assembly, and includes the transition duct arranged downstream of a first reaction zone belonging to the first burner group, the first reaction zone having a round cross sectional shape, and wherein the first burner group, the at least one second burner, the first reaction zone, a second reaction zone belonging to the at least one second burner, and the transition duct are located within each of the plurality of combustion chamber elements, wherein the plurality of combustion chamber elements are arranged around the at least one rotor, and are configured during operation to maintain with respect to one another either an autonomous or quasi-autonomous sequential combustion, wherein each of the transition ducts has a cross sectional shape, which is round, oval, or elliptical, and wherein the cross sectional shape of the transition duct contracts from the cross sectional shape of the first reaction zone and expands to a rectangular cross sectional shape, and wherein each of the second reaction zones has the rectangular cross sectional shape, the method comprising:
sequentially operating the first burner group and the at least one second burner in a direction of a flow of a combustion path within a tubular each of the plurality of combustion chamber element elements extending between the at least one compressor and the at least one turbine;
arranging the transition duct downstream of a first reaction zone belonging to the first burner group;
introducing part of a compressor air and/or a steam quantity and/or another gas into combustion gases originating from the first burner group at the transition duct of each of the plurality of combustion chamber elements;
cooling the combustions gases from the first burner group in the transition duct to 900° C. to 1100° C.; and
autoigniting an injected fuel from the at least one second burner with the combustion gases from the first burner group.

12. The method as claimed in claim 11 , comprising:
using a calorific potential of exhaust gases from the gas turbine assembly for operating a steam circuit.

13. The method as claimed in claim 11 , comprising:
cooling the combustion gases from first combustion in an intermediate transition duct downstream of the first reaction zone belonging to the first burner group and upstream of the at least one second burner.

14. The method as claimed in claim 13 , comprising:
cooling the combustion gases from first combustion with a heat exchanger in the intermediate transition

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Marmilic Robert
• Hellat Jaan
• Freitag Ewald
• Eroglu Adnan

Classifications

• F02C7/228

  Dividing fuel between various burners · CPC title

• F23C6/04

  in series connection (consuming smoke or fumes in separate combustion apparatus F23G7/06) · CPC title

• F02C7/141 Primary

  of working fluid · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title

• F23R3/346

  for staged combustion · CPC title