Honeywell International Inc.

United Technologies Corporation

William E Alford

Gabriel L Suciu

Brian D Merry

Morris G Anderson

Om Parkash Sharma

Ron Haugland

David K Winstanley

Michael LaMar Trego

Michael L Trego

Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.

Cooling systems for use on aircraft

A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.

Leaned high pressure compressor inlet guide vane

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Mesa, AZ, United States of America

William E Alford