Gas turbine engine shaft bearing configuration
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United States of America Patent
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Nov 24, 2015
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N/A
app pub date -
Mar 19, 2014
filing date -
Jan 31, 2012
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Abstract
A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.
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