GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT
摘要
A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.
申请公布号
WO2014078003(A2)
申请公布日期
2014.05.22
申请号
WO2013US65337
申请日期
2013.10.17
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
SUCIU, GABRIEL L.;EPSTEIN, ALAN H.;LORD, WESLEY K.;CHANDLER, JESSE M.