TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM
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United States of America Patent
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Issued Date -
Oct 30, 2014
app pub date -
Apr 26, 2013
filing date -
Apr 26, 2013
priority date (Note) -
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Abstract
A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart.
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