Gas turbine power plant with non-homogeneous input gas

Patent metadata

Field	Value
Publication number	US-9664110-B2
Application number	US-201414492222-A
Country	US
Kind code	B2
Filing date	Sep 22, 2014
Priority date	Mar 24, 2012
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

The invention relates to a method for operating a gas turbine which includes a compressor with annular inlet area, at least two burners, a combustion chamber and a turbine. According to the method, at least one first partial intake flow, consisting of oxygen-reduced gas which has an oxygen concentration which is lower than the average oxygen concentration of the compressor intake flow, and at least one second partial intake flow, consisting of fresh air, are fed to the compressor in an alternating manner in the circumferential direction of the inlet area. In addition, the invention relates to a gas turbine power plant with a gas turbine, the compressor inlet of which includes at least one first segment and at least one second segment which are arranged in an alternating manner around a compressor inlet in the circumferential direction, wherein a feed for an oxygen-reduced gas is connected to the first segment and a fresh air feed is connected to the second segment of the compressor inlet.

First claim

The invention claimed is:

1. A method for operating a gas turbine having a compressor with an inlet, at least two burners, a combustion chamber and a turbine, the method comprising:
feeding at least one first partial intake flow, consisting of oxygen-reduced gas which has an oxygen concentration which is lower than an average oxygen concentration of a compressor intake flow, and at least one second partial intake flow, consisting of fresh air, to the compressor in an alternating manner in a circumferential direction of the inlet.

2. The method as claimed in claim 1 , wherein the alternating manner of feeding oxygen-reduced gas and fresh air is carried out via an inner sector of an inlet cross section relative to a rotational axis of the compressor and fresh air is fed via an outer sector of the inlet cross section relative to the rotational axis of the compressor.

3. The method as claimed in claim 1 , wherein the alternating manner of feeding oxygen-reduced gas and fresh air is carried out via an inner sector of an inlet cross section relative to a rotational axis of the compressor and oxygen-reduced gas is fed via an outer sector of the inlet cross section relative to the rotational axis of the compressor.

4. The method as claimed in claim 1 , wherein a first partial intake flow, consisting of oxygen-reduced gas, is directed in each case into one burner, or into an integral multiple of adjacent burners, downstream of the compressor.

5. The method as claimed in claim 1 , wherein a second partial intake flow, consisting of fresh air, is directed in each case into one burner, or into an integral multiple of adjacent burners, downstream of the compressor.

6. The method as claimed in claim 1 , wherein a fuel feed to a burner which is supplied with oxygen-reduced gas compared with a fuel feed to a burner which is supplied with fresh air is reduced so that hot combustion gases at an outlet of the burners have the same oxygen concentration.

7. The method as claimed in claim 1 , wherein the inlet of the compressor, to which is connected a flow passage of the compressor, is split into at least one first segment and at least one second segment, outlets of which are arranged in an alternating manner around an annular area of the flow passage in the circumferential direction of the inlet, wherein fresh air is fed in each case via the at least one first segment and oxygen-reduced gas is fed via the at least one second segment in an alternating manner.

8. The method as claimed in claim 1 , wherein flue gases of the gas turbine are split into a first flue gas flow for recirculation into an intake flow of the gas turbine and into a second flue gas partial flow for discharging to an environment, and in that the oxygen-reduced gas comprises a recirculated first flue gas flow of the gas turbine.

9. A gas turbine power plant comprising:
a gas turbine with a compressor inlet, at least two burners, a combustion chamber and a turbine, wherein an annular inlet area of the compressor, to which is connected a flow passage of the compressor, comprises at least one first segment and at least one second segment which are arranged in an alternating manner around an annular area of the flow passage in a circumferential direction of the compressor inlet,
wherein a feed for an oxygen-reduced gas, which has an oxygen concentration which is lower than an average oxygen concentration of a compressor intake flow during operation of the gas turbine, is connected to the at least one first segment of the compressor inlet, and a fresh air feed is connected to the at least one second segment of the compressor inlet.

10. The gas turbine power plant as claimed in claim 9 , wherein the compressor inlet, to which is connected the flow passage of the compressor, comprises an inner sector relative to a rotational axis of the compressor and an outer sector relative to the rotational axis of the compressor, wherein alternating first segments and second segments are arranged in the inner sector of an inlet cross section relative to the rotational axis of the compressor.

11. The gas turbine power plant as claimed in claim 10 , comprising:
a control element by means of which an area ratio of a sum of connecting areas of the at least one first segment to the flow passage of the compressor to sum of connecting areas of the at least one second segment to the flow passage of the compressor can be varied in order to adapt respective area ratios to changes in a ratio between supplied fresh air and oxygen-reduced gas.

12. The gas turbine power plant as claimed in claim 10 , wherein the gas turbine power plant comprises an exhaust gas splitter for splitting flue gas flow of the gas turbine into a first flue gas partial flow, for recirculation into an intake flow of the gas turbine, and into a second flue gas partial flow for discharging to an environment, and also comprises a recirculation line which connects the exhaust gas splitter to at least one first segment of the compressor inlet.

13. The gas turbine power plant as claimed in claim 9 , wherein the compressor inlet, to which is connected the flow passage of the compressor, comprises an inner sector relative a rotational axis of the compressor and an outer sector relative to the rotational axis of the compressor, wherein alternating first segments and second segments are arranged in the outer sector of an inlet cross section relative to the rotational axis of the compressor.

14. The gas turbine power plant as claimed in claim 9 , wherein an integral multiple of burners are arranged per first segment of the compressor, and an integral multiple of burners are arranged per second segment.

15. The gas turbine power plant as claimed in claim 9 , wherein a multiplicity of feed passages from feed holes in bearing supports of the compressor for introduction of oxygen-reduced gas are arranged in the compressor inlet concentrically to an axis of the gas turbine in a circumferentially distributed manner.

Assignees

• Alstom Technology Ltd
• Ansaldo Energia Switzerland AG

Inventors

• Guethe Felix
• Poyyapakkam Madhavan Narasimhan
• Graf Frank
• Schuermans Bruno
• Benz Eribert

Classifications

• F23R3/26

  Controlling the air flow · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F02C3/13

  having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} · CPC title

• F23C2202/30

  Premixing fluegas with combustion air · CPC title

• F23R3/04

  Air inlet arrangements · CPC title