Two-shaft engine for an aircraft gas turbine
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United States of America Patent
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Jan 24, 2012
Grant Date -
Apr 1, 2010
app pub date -
May 15, 2009
filing date -
May 16, 2008
priority date (Note) -
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Abstract
On a two-shaft engine for an aircraft gas-turbine with a central low-pressure shaft, with a high-pressure shaft co-axially surrounding the low-pressure shaft and with bearing units supporting the shafts on the engine casing, the bearing loads of the high-pressure shaft are directed upstream towards the fan and the bearing loads of the low-pressure shaft are directed downstream. In order to reduce axial bearing load of the high-pressure bearing unit, the oppositely directed bearing loads of the low-pressure shaft (3) and of the high-pressure shaft (6) partly compensate one another, in that the front thrust bearing unit (10) of the high-pressure shaft (6) is supported on the engine casing (1) and the front thrust bearing unit (12) of the low-pressure shaft (3) is supported on the high-pressure shaft (6).
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