Cantilevered stator stage
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United States of America Patent
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Jul 10, 2007
Grant Date -
Jul 14, 2005
app pub date -
Dec 30, 2004
filing date -
Jan 13, 2004
priority date (Note) -
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Abstract
A cantilevered stator stage for the axial compressor 14 of a gas turbine engine 10 in which the stator tips 26 rub against an abrasive section 24 on the rotor drum 22 during initial running of the engine 10 to abrade the tips 26 of the stator to provide optimised stator tip running clearance.
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