Honeywell International Inc.

Ron Haugland

Morris G Anderson

Yufei Xiong

Craig E Thompson

Ernest Kurschat

William E Alford

Michael LaMar Trego

David K Winstanley

Michael L Trego

An engine system for starting a gas turbine engine includes a starter coupled to the gas turbine engine and configured to provide torque to the gas turbine engine; and a controller coupled to the starter and configured to evaluate an engine system parameter and to select from a plurality of start modes for starting the gas turbine engine based on the engine system parameter.

Engine systems with enhanced start control schedules

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

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Scottsdale, AZ, United States of America

Ron Haugland