LPC flowpath shape with gas turbine engine shaft bearing configuration
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United States of America Patent
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May 26, 2015
Grant Date -
Sep 4, 2014
app pub date -
Oct 30, 2013
filing date -
Jan 31, 2012
priority date (Note) -
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status (Latency Note)
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Abstract
A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
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