Gas turbine engine with bearing chambers and barrier air chambers
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United States of America Patent
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Mar 18, 1997
Grant Date -
N/A
app pub date -
Nov 30, 1995
filing date -
Apr 1, 1993
priority date (Note) -
In Force
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Abstract
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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