Gas turbine engine bearing arrangement
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United States of America Patent
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Apr 30, 2002
Grant Date -
N/A
app pub date -
Feb 18, 2000
filing date -
Feb 25, 1999
priority date (Note) -
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status (Latency Note)
Importance
Abstract
A gas turbine engine (10) is provided with a plurality of shafts (18, 19, 20) interconnecting its compressor portions (11, 12, 13) with its turbine portions (15, 16, 17). Each shaft (18, 19, 20) is supported in the hotter part of the engine by electromagnetic bearings (26, 28, 32) and by rolling element bearings (24, 27, 29, 31, 33) in the remainder of the engine (10). The arrangement provides a simplified liquid lubrication system for the rolling element bearings (24, 27, 29, 31, 33) which reduces the likelihood of lubricant thermal degradation of the lubricant.
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