Rolls-Royce Corporation

Rolls-Royce North American Technologies Inc.

Jacob W Harral

Michael Joseph Kabbes

Michael Dornfeld

Peter Michael Schenk

Mathew Hill

Erik Alexander Munevar

Phillip Burnside

Jeffrey Lawrence

Brian Joseph Huber

Douglas Keith Schetzel, Ii

Derek Mitchell

Kenneth Miller

A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.

Emergency start of a gas turbine engine

A system includes a gas turbine engine configured to provide propulsion to an aircraft and a starter system configured to start the gas turbine engine. The starter system comprises a motor controller and a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine. The closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid. The cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine.

Motor and motor controller thermal management features

A centrifugal air-oil separator system for a gas turbine engine system is described. The air-oil separator system has a rotatable shaft and the shaft includes an axially extending bore formed at least partially through the shaft. A gear is integral to or mounted on an outer surface of the shaft. The air-oil separator system also includes a bolt-on breather mounted on the shaft and independent from and in contiguous contact with the gear to assist in separating the oil from the air. Various types of materials may be utilized in the construction of the air-oil separator system.

Shaft mounted centrifugal air-oil separator system

Scavenge systems for a gas turbine engine including a valve positioned at a first drainage outlet of an enclosure to selectively open and evacuate liquid from the cavity through the first drainage outlet in response to the valve being submerged in liquid are provided. Methods of reducing suction of air from an enclosure of a cavity of a gas turbine engine are further provided.

Flow draining enhancement system for engine sump cavities

In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

Offset clutch mechanism for electric starting and barring motor of a gas-turbine engine

A forced air supply system is provided to deliver forced air to fluid or a mixture of fluid and air in an enclosure of a cavity of a gas turbine engine when the gas turbine engine experiences a negative-gravity force event. Methods are also provided for removing fluid and/or air from the enclosure when the gas turbine engine experiences the negative-gravity force.

Forced air supply system for engine cavity under negative-G force

A gas turbine engine test assembly includes a test apparatus having a rotor and stator and a bearing assembly having a fluid circuit providing an adjustable fluid pressure interface between the rotor and stator.

Gas turbine engine test stand

A sump assembly for use in a gas turbine engine includes a housing and a shaft assembly. The housing is arranged about a central axis of the sump assembly to define a cavity configured to house oil and high-pressure gasses. The shaft assembly is mounted to rotate about the central axis and to direct the high-pressure gasses into the housing.

Engine sump with air separation features

A sealing element for a shaft coupling is disclosed. The sealing element may include an annular seal body and a plurality of projections circumferentially spaced around the seal body. One or more of the plurality of projections may include at least one of an axial component extending longitudinally in an axial direction from the seal body and/or a radial component extending radially inwards from the seal body towards the center axis. The sealing element is configured to retrofit into existing standard o-ring grooves and provides optimal lubrication, for example in a spline joint, by keeping the spline joint contact area submerged in lubricant and includes heat and debris removal with lubricant flow-through.

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Brownsburg, IN, United States of America

Jacob W Harral