Gas Turbine Engine With Inlet Particle Separator and Thermal Management

Abstract

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.

1 . A gas turbine engine comprising:
 a nose cone at an inlet end, and spaced radially inwardly of a nacelle;   a compressor downstream of said nose cone, and a core inlet for delivering air downstream of said nose cone into said compressor; and   an inlet particle separator including a manifold for delivering air radially outwardly of said core inlet, said air delivered by the inlet particle separator passing over a heat exchanger before passing to an outlet.   
     
     
         2 . The gas turbine engine as set forth in  claim 1 , wherein said heat exchanger cools oil associated with a gear reduction on the gas turbine engine. 
     
     
         3 . The gas turbine engine as set forth in  claim 1  wherein said compressor rotating about a central axis of the engine, and said nose cone has a radially outermost portion which is radially outward of a radially inner end of said core inlet, and such that air having heavier particles is generally directed radially outwardly of said core inlet and into said inlet particle separator. 
     
     
         4 . The gas turbine engine as set forth in  claim 1 , wherein said manifold extends for 360 degrees about said axis of rotation. 
     
     
         5 . The gas turbine engine set forth in  claim 4 , wherein said manifold having an open inlet at an upstream end, and a downstream outlet over a limited portion of the 360 degrees of the circumferentially extending portion. 
     
     
         6 . The gas turbine engine as set forth in  claim 1 , wherein an ejector is positioned downstream of said heat exchanger, said ejector for selectively driving air across the heat exchanger. 
     
     
         7 . The gas turbine engine as set forth in  claim 1 , wherein a turbine section is downstream of said compressor and drives propellers.