Combustor for gas turbine

F - Mech Eng,Light,Heat,Weapons – 23 – R

Patent

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Details

F23R 3/42 (2006.01) F02C 7/18 (2006.01) F23R 3/04 (2006.01) F23R 3/06 (2006.01)

Patent

CA 2433402

A ring (100) for forming a cooling-air layer is attached to the liner (11) of a combustion chamber, to supply cooling air fed from a compressor from a cooling-air supply hole (41). During the operation of a gas turbine, the cooling air is allowed to flow from a gap (51) formed between the ring (100) and the inner surface of the liner (11) of the combustion chamber, to form the cooling-air layer on the inner surface of the liner (11) of the combustion chamber.

L'invention concerne un dispositif combustor de turbine à gaz. Un anneau (100) donnant forme à une couche d'air de refroidissement est adapté à un tube interne de chambre de combustion (11). L'air de refroidissement qui émane d'un compresseur, via un trou d'alimentation correspondant (41), est fourni à l'anneau: cet air s'écoule depuis un espace (51) constitué par l'anneau (100) et la surface de paroi intérieure du tube (11) susmentionné, au cours du fonctionnement de la turbine à gaz, formant la couche d'air de refroidissement sur la surface de paroi interne du tube (11) en question.

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