Rolls-Royce Corporation

Rolls-Royce North American Technologies Inc.

Douglas Michael Roever

Robert Zeller

Gregory Blake

Mark Potter

Christopher John Norris

Michael S Dornfeld

A gas turbine engine assembly and a method for assembling a gas turbine engine assembly are disclosed herein. The gas turbine engine assembly includes an engine core and a gearbox. The gearbox includes a lubrication system having a first sump and a second sump. The lubrication system is configurable to provide oil from either of the first and second sumps in various configurations of the gas turbine engine assembly.

Reconfigurable lubrication system for multiple powertrain orientations

Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

Electrical assist for aircraft

The present invention contemplates a face coupling, and contemplates a gas turbine engine having a face coupling. The face coupling includes a plurality of driving teeth extending from a first component, and a plurality of driven teeth extending from a second component. The plurality of driving teeth and the plurality of driven teeth cooperate to transmit a torque load from the first component to second component. The plurality of driven teeth include a root transition for preventing a driving tooth tip edge from contacting an adjacent driven tooth.

Face coupling

A system for balancing a rotatable gas turbine engine component. The system includes two balance rings that are coupled to the component by mating splines on the respective item. Each of the rings has a mass asymmetry that is indexable relative to the primary component to achieve the imbalance correction.

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Indianapolis, IN, United States of America

Douglas Michael Roever