F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 9/02 (2006.01) F01D 5/08 (2006.01) F01D 9/04 (2006.01) F01D 9/06 (2006.01) F02C 3/04 (2006.01) F02C 7/08 (2006.01) F04D 27/02 (2006.01) F23R 3/54 (2006.01)
Patent
CA 2345341
A gas turbine engine includes a compressor (12), a combustor (16) receiving with a part (A) of the compressed air, and a turbine rotor disk (14). A part (B) of the compressed air is bled from the compressor (12) and directly bypassed through a passage (30) to a zone (32) of the turbine rotor disc (14). Vanes (34) located inthe passage (30) impart a spin to the air (B), which is fed for driving the turbine rotor disc (14) into passages (36) of the turbine blades (15), thereby cooling them, and is consequently ejected into an annular zone (38) and then into an entry zone (19) of the combustor (16). Fuel is fed at ports (18) into this spinning heated air flow (C). The heated fluid (C) is then mixed with the incomming compressed air (A) for combustion. The exhaust gases are eventually directed through the turbine.
L'invention concerne un moteur de turbine à gaz, comprenant un dispositif qui admet un écoulement fluidique rotatif provenant d'un espace annulaire d'un boîtier et se dirigeant vers une partie d'entrée d'une chambre de combustion, afin de former un écoulement fluidique rotatif dans ladite partie d'entrée de la chambre de combustion. L'écoulement fluidique rotatif est formé dans l'espace annulaire du boîtier par fourniture d'un fluide aux pales du disque de rotor de turbine, à partir de la chambre de combustion.
Alm Development Inc.
Smart & Biggar
LandOfFree
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