Cooling and damping arrangement for gas turbine bearings
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United States of America Patent
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Jun 13, 1989
Issued Date -
N/A
app pub date -
Apr 25, 1988
filing date -
Feb 14, 1986
priority date (Note) -
Expired
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Abstract
A rotor bearing on the turbine side of a gas turbine is surrounded by a concentric cavity through which fuel is routed from its source to the turbine combustion chamber. The fuel of the gas turbine is used as the coolant for the rotor bearing and at the same time the concentric cavity surrounding the bearing forms a hydraulic 'compression' film damping device.
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