Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Christopher Banham

Rex M Little

Douglas J Snyder

Timothy Unton

Melissa Hughes

Brian R Bennett

Jason Lee Swindle

Jason Swindle

Cooling systems and methods of operation are provided. The cooling system may include a two-phase pumped loop (TPPL). The two-phase pumped loop may include, a receiver, a pump downstream from the receiver, a heat load downstream from the pump, a TPPL tee downstream from the heat load, a TPPL check valve downstream from the TPPL tee, and a heat exchanger downstream from the TPPL check valve and upstream from the receiver. The cooling system may further include a vapor cycle system (VCS) loop. The vapor cycle system loop may include the receiver, a compressor downstream from a vapor outlet of the receiver, a compressor check valve downstream from the compressor and upstream of the heat exchanger, the heat exchanger, and the heat load downstream from a liquid outlet of the receiver.

Bimodal cooling system

In some examples, an electric machine system including an outer housing; a stator assembly within the outer housing; a corrugated ring located between the stator assembly and the outer housing, the corrugated ring defining a gap between the stator assembly and the outer housing; and a pump configured to transfer a fluid through the gap between the stator assembly and housing to remove heat from at least one of the stator assembly or outer housing.

Electric machine with fluid cooled stator assembly

A gas turbine engine coupled to an aircraft includes an engine core arranged axially along an axis, a bypass duct arranged circumferentially around the engine core to define a bypass channel, and a heat exchanger system. The bypass channel is arranged to conduct bypass air around the engine core to provide thrust for the gas turbine engine. The heat exchanger system is configured to provide cooling for the engine core.

Bypass duct conformal heat exchanger array

Gas turbine engines which include electrical motor-generator assemblies arranged near the fan outlet include electrical cable routing assemblies extending through a bypass flow path. Directing the electrical cables through a king guide vane can consolidate routing requirements while accessing each of electrical windings of the electrical machine.

Routing for electrical communication in gas turbine engines

According to one aspect, a genset includes a gas turbine engine having a low pressure shaft wherein the gas turbine engine is adapted to provide mechanical power to a propulsion type load. The genset further includes a generator having an input power shaft wherein the generator is adapted to receive mechanical power to develop electric power. The genset further includes an output power shaft having a first end coupled to the low pressure shaft of the gas turbine and a second end coupled to the input power shaft of the generator and a plurality of struts wherein the first ends of the plurality of struts are coupled to the gas turbine engine and second ends of the plurality of struts are coupled to the generator at locations substantially aligned with a center of gravity of the generator. A suspension apparatus attaches the gas turbine engine and the generator at mounting locations substantially aligned with a gas turbine engine center of gravity and at mounting locations substantially aligned with the generator center of gravity, respectively.

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Indianapolis, IN, United States of America

Christopher Banham