Rolls-royce Corporation

Light Engineering Corporation

Richard Lex Seneff

Andrew D Hirzel

One embodiment of the present invention is a unique gas turbine engine blade. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and blades. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Gas turbine engine and blade for gas turbine engine

A composite rotor for an axial airgap, permanent magnet dynamoelectric machine comprises a plurality of magnet subassemblies adhesively bonded together to form the rotor. Each magnet subassembly comprises a rotor permanent magnet and an optional spacer. A fibrous belt is wrapped around the periphery of each subassembly to provide high tensile strength at least along the radial sides of the subassembly. The belt is preferably infiltrated with an adhesive agent, such as an epoxy resin, that is used to bond the subassemblies. The rotor is thereby provided with high strength and low mass, making it suitable for use in a high-speed, high pole count electric machine.

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Indianapolis, IN, United States of America

Richard Lex Seneff