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1. WO2015153115 - AIR FUEL PREMIXER FOR LOW EMISSIONS GAS TURBINE COMBUSTOR

Publication Number WO/2015/153115
Publication Date 08.10.2015
International Application No. PCT/US2015/021130
International Filing Date 18.03.2015
IPC
F23R 3/14 2006.1
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
10for primary air
12inducing a vortex
14by using swirl vanes
F23R 3/28 2006.1
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
CPC
F05D 2240/35
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2240Components
35Combustors or associated equipment
F23R 3/14
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
10for primary air
12inducing a vortex
14by using swirl vanes
F23R 3/286
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
286having fuel-air premixing devices
Applicants
  • GENERAL ELECTRIC COMPANY [US]/[US]
Inventors
  • LI, Suhui
  • JOSHI, Narendra, Digamber
  • MCMANUS, Keith, Robert
Agents
  • TOPPIN, Catherine, J.
Priority Data
14/243,95103.04.2014US
Publication Language English (en)
Filing Language English (EN)
Designated States
Title
(EN) AIR FUEL PREMIXER FOR LOW EMISSIONS GAS TURBINE COMBUSTOR
(FR) DISPOSITIF DE PRÉMÉLANGE AIR-CARBURANT POUR CHAMBRE DE COMBUSTION DE TURBINE À GAZ À FAIBLES ÉMISSIONS
Abstract
(EN) A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct, an outer annular swirler located adjacent an upstream end of the mixing duct for swirling air flowing therethrough in a first swirl direction and an inner annular swirler located adjacent of the mixing duct upstream end for swirling air flowing therethrough in a second swirl direction. The system includes a hub separating said inner and outer annular swirlers to permit independent rotation of an air stream therethrough and multiple hollow paths located radially outward around the centerbody fuel injector and at a radially inward side of the inner annular swirler for allowing a flow of sweeping air over the surface of the centerbody fuel injector.
(FR) L'invention concerne un système pour prémélanger du carburant et de l'air avant combustion dans un moteur à turbine à gaz, comprenant un conduit de mélange, un injecteur de carburant de corps central situé le long d'un axe central du conduit de mélange, un dispositif de turbulence annulaire externe situé adjacent à une extrémité en amont du conduit de mélange pour faire tourbillonner l'air qui le traverse dans une première direction de tourbillonnement et un dispositif de turbulence annulaire interne situé adjacent à l'extrémité en amont du conduit de mélange pour faire tourbillonner l'air le traversant dans une seconde direction de tourbillonnement. Le système comprend un moyeu séparant lesdits dispositifs de turbulence annulaires interne et externe pour permettre une rotation indépendante d'un flux d'air à travers celui-ci et plusieurs trajectoires creuses situées en sens radial vers l'extérieur autour de l'injecteur de carburant de corps central et au niveau d'un côté radialement vers l'intérieur du dispositif de turbulence annulaire interne pour permettre un écoulement d'air de balayage au-dessus de la surface de l'injecteur de carburant de corps central.
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