| 摘要 |
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 turbin e blades (15), thereby cooling them, and is consequently ejected into an annul ar zone (38) and then into an entry zone (19) of the combustor (16). Fuel is fe d at ports (18) into this spinning heated air flow (C). The heated fluid (C) i s then mixed with the incomming compressed air (A) for combustion. The exhaust gases are eventually directed through the turbine.
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