Gas-turbine engine with bearing chambers and barrier-air...

Details Gas-turbine engine with bearing chambers and barrier-air... Gas-turbine engine with bearing chambers and barrier-air...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/18 (2006.01) F01M 3/00 (2006.01) F02C 7/06 (2006.01)

Patent

CA 2159634

An aircraft gas turbine has a barrier air flow produced by the fan or a low-pressure compressor which passes continuously through the compressor bearing chamber, while the turbine bearing chamber is supplied with barrier air by the high-pressure compressor. The barrier air flow drawn from the turbine bearing chamber passes into an ejector which is also connected to the compressor bearing chamber so that, when the pressure is insufficient, the barrier air flow is drawn-off by the ejector.

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