| 摘要 |
The invention concerns, in particular, aircraft gas turbines and proposes that a barrier-air flow produced by the fan or a low-pressure compressor 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 level is insufficient, the barrier-air flow is drawn off by the ejector. |
