Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Rex M Little

Steven Mazur

Christopher Banham

Brandon R Snyder

Brett Hartnagel

Trevor C Pfeil

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and a tip clearance system. The tip clearance system includes a tip clearance sensor located in an annular plenum defined between an inner case and an outer case included in the case assembly. The tip sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Turbine assembly with case-integrated cooled clearance measurement system

A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

Gas turbine engine centrifugal compressor with impeller load and cooling control

A thermal management system for a gas turbine engine includes an inlet, a compressor, a mixing unit, and a fuel source. The compressor includes a low pressure stage and a high pressure stage. The mixing unit includes a first valve port fluidically connected to a low pressure bleed line of the compressor and a high pressure bleed line of the compressor and having an adjustable inlet gate on each of these lines and an outlet fluidically connected to the inlet of the engine to prevent ice accretion in the inlet or de-ice the inlet. The fuel source is configured to provide fuel to the mixing unit to actuate the adjustable inlet gates to regulate the amounts of low pressure bleed air and high pressure bleed air directed to the outlet.

Anti-ice mixing unit utilizing bleed air for a gas turbine engine

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.

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Indianapolis, IN, United States of America

Rex M Little