A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.
申请公布号
WO2014123626(A2)
申请公布日期
2014.08.14
申请号
WO2013US75623
申请日期
2013.12.17
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
JONES, ANTHONY C.;TRAVELBEE, CHARLES BRIAN;LYDON, PATRICK M.;ALEXANDER, ERIC J.;THAYALAKHANDAN, NAGAMANY