Gas turbine combustor

Details Gas turbine combustor Gas turbine combustor

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/22 (2006.01) F02C 7/04 (2006.01) F23R 3/10 (2006.01)

Patent

CA 2246218

In gas turbine combustor constructed by combustion chamber (10) and steam-cooled peripheral wall (2) thereof, there is bored air hole (1) for injecting dilution air therethrough in the peripheral wall (2) on upstream side of the combustion chamber (10), thereby the air is supplied through the air hole (1) into the vicinity of inner surface of the peripheral wall (2) to form film flow of air and increase of fuel concentration there is suppressed. The dilution air is preferably supplied from gas turbine compressor (6).

Dans le dispositif combustor d'une turbine à gaz défini par la chambre de combustion (10) et sa paroi périphérique refroidie à la vapeur (2), il y a un trou d'air (1) percé dans la paroi périphérique (2) pour injecter de l'air de dilution du côté amont de la chambre de combustion (10), et ainsi l'air est amené par le trou d'air (1) au voisinage de la surface intérieure de la paroi périphérique (2) pour former un flux d'air et l'augmentation de la concentration de combustible à cet endroit est supprimée. L'air de dilution provient de préférence du compresseur (6) de la turbine à gaz.

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