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1. WO2013143975 - GAS TURBINE POWER PLANT WITH NON-HOMOGENEOUS INPUT GAS

Publication Number WO/2013/143975
Publication Date 03.10.2013
International Application No. PCT/EP2013/055991
International Filing Date 21.03.2013
IPC
F02C 7/08 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
08Heating air supply before combustion, e.g. by exhaust gases
F02C 3/34 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
34with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F23R 3/28 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
F23R 3/34 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
34Feeding into different combustion zones
CPC
F02C 3/13
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
04having a turbine driving a compressor
13having variable working fluid interconnections between turbines or compressors or stages of different rotors
F02C 3/34
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
34with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 7/08
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
08Heating air supply before combustion, e.g. by exhaust gases
F23C 2202/30
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  ; A CARRIER GAS OR; AIR 
2202Fluegas recirculation
30Premixing fluegas with combustion air
F23C 9/00
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  ; A CARRIER GAS OR; AIR 
9Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
F23R 3/04
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
Applicants
  • ALSTOM TECHNOLOGY LTD [CH]/[CH]
Inventors
  • GUETHE, Felix
  • POYYAPAKKAM, Madhavan Narasimhan
  • GRAF, Frank
  • SCHUERMANS, Bruno
  • BENZ, Eribert
Priority Data
12161146.124.03.2012EP
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) GAS TURBINE POWER PLANT WITH NON-HOMOGENEOUS INPUT GAS
(FR) INSTALLATION TURBOMOTRICE À TURBINE À GAZ FONCTIONNANT AVEC UN GAZ D'ENTRÉE NON HOMOGÈNE
Abstract
(EN)
The invention relates to a method for operating a gas turbine (6) which comprises a compressor (1) with annular inlet area, at least two burners, a combustion chamber (4, 14, 15) and a turbine (7, 16, 17). According to the method, at least one first partial intake flow, consisting of oxygen-reduced gas (21) 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 (2), are fed to the compressor (1) 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 (6), the compressor inlet (3) of which comprises at least one first segment (51) and at least one second segment (52) which are arranged in an alternating manner around a compressor inlet in the circumferential direction, wherein a feed for an oxygen-reduced gas (21) is connected to the first segment (51) and a fresh air feed is connected to the second segment (52) of the compressor inlet (3).
(FR)
L'invention concerne un procédé pour faire fonctionner une turbine à gaz (6) comprenant un compresseur (1) ayant une zone d'entrée annulaire, au moins deux brûleurs, une chambre de combustion (4, 14, 15) et une turbine (7, 16, 17). Selon le procédé, au moins un premier flux d'admission partiel, constitué d'un gaz réduit en oxygène (21) ayant une concentration d'oxygène inférieure à la concentration moyenne d'oxygène du flux d'admission du compresseur, et au moins un second flux d'admission partiel, constitué d'air frais (2), sont amenés au compresseur (1) de manière alternée dans la direction circonférentielle de la zone d'entrée. En outre, l'invention concerne une installation turbomotrice à turbine à gaz dotée d'une turbine à gaz (6), dont l'entrée de compresseur (3) comprend au moins un premier segment (51) et au moins un second segment (52) disposés de manière alternée autour d'une entrée de compresseur dans la direction circonférentielle, une alimentation pour un gaz réduit en oxygène (21) étant raccordée au premier segment (51) et une alimentation en air frais étant raccordée au second segment (52) de l'entrée de compresseur (3).
Latest bibliographic data on file with the International Bureau