Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Andrew D Copeland

Al Cookerly

Craig M Price

Edward Claude Rice

John Munson

John Gebhard

Donald W Burns

Adam L Kempers

Kevin Beckner

Matthew Tyler Bouton

Stanford O Clemens

Gregory Blake

Tony Snyder

Joel M Rubel

John M Flynn

Molly Harrison

Phillip S Burkholder

Craig Price

Alan B Cookerly

An aircraft includes a first propulsion unit, a second propulsion, and a controller configured to increase thrust output in one of the first propulsion unit or the second propulsion unit in response to a detected thrust reduction from the other of the first propulsion unit. Each of the first propulsion unit and the second propulsion unit include a rotor driven by a gas turbine engine with a drive shaft, an output shaft coupled between the drive shaft and the driven rotor and a mechanical coupler for decoupling the output shaft from the drive shaft.

Limited slip torque-limiter coupling

A rotor assembly includes an oil jet assembly, an inner shaft assembly, an outer shaft assembly, and an oil mist shield. The oil jet assembly selectively ejects oil for lubrication. The inner shaft assembly is configured to rotate about a central axis. The outer shaft assembly is configured to rotate selectively about the central axis independent of the inner shaft assembly. The oil mist shield is coupled with the outer shaft and is configured to selectively block and allow the oil from the oil jet assembly from passing into a cavity.

Centrifugally operated oil shield for lubrication flow control

A gas turbine engine includes a first spool and a second spool. The first spool includes a compressor stage, a first turbine stage, and a first shaft configured to transmit rotational energy between the first turbine stage and the compressor stage. The second spool includes a fan, a second turbine stage, and a second shaft configured to transmit rotational energy between the second turbine stage and the fan.

Gas turbine engine system with synchronization features for gearbox operation

A magnetic squeeze film damper system comprises a bearing assembly having an outer race with a first outer surface and a first inner surface and a bearing located along the first inner surface. The system further comprises a squeeze film damper housing having a second outer surface and a second inner surface that is contiguous with the first outer surface. A channel having a forward end and an aft end is defined within the housing along the second inner surface, the channel bordered by the first outer surface. The system further includes a first seal gland located along the forward end of the channel and a second seal gland located along the aft end of the channel. Both seal glands comprise a reservoir for holding a magneto-rheological fluid, the reservoir encased in an elastomer. At least one electromagnet is arranged in close proximity to each of the seal glands.

Magnetic squeeze film damper system for a gas turbine engine

An expendable bearing and a method for making the same including an inner race defining an inner bearing diameter, an outer race defining an outer bearing diameter, a seal attached to the outer race and positioned adjacent and in contact with the inner race, where the inner race, the outer race, and the seal define a bearing cavity, a plurality of rolling elements positioned adjacent to the inner and outer races in the bearing cavity, a dry film lubricant on a surface of at least one of the inner race, the outer race, or the plurality of rolling elements, and a powder lubricant comprising carbon nanotubes disposed in the bearing cavity.

Lubrication for an expendable bearing

A clutch for use in a gas turbine engine is disclosed herein. The clutch is adapted to selectively transmit rotation from a first shaft of the clutch to a second shaft of the clutch.

Clutch with redundant engagement systems

A bearing assembly includes an outer race, a cage, a plurality of internal rotating members, and an inner race. Lubricant flows through the bearing assembly to withdraw heat generated during operation of the bearing assembly.

High speed bearing assembly

A seal assembly for use in a gas turbine engine includes a first component, a second component, and a sealing unit. The first component is spaced apart from the second component to form a gap therebetween. The sealing unit is positioned in the gap between the first and second components to block liquids and/or gasses from traveling through the gap.

Seals for a gas turbine engine

A gas turbine engine is provided that includes a gearbox operable to selectively couple a relatively high pressure spool shaft to a relatively low pressure spool shaft. In one form the gearbox includes a cone clutch that engages a male member of the cone clutch to a female member of the cone clutch during an engine start of the gas turbine engine. A relatively high pressure of a working fluid can be used to bring the male member and the female member together. A spring can also be used to urge the male member and the female member apart when the working fluid is at a relatively low pressure.

Gas turbine engine shaft coupler

A turbine engine is disclosed herein. The turbine engine includes a starter/generator operable to deliver rotational power in a first mode of operation and to generate electrical power in a second mode of operation. The turbine engine also includes an accessory gear box mechanically coupled to the starter/generator. The turbine engine also includes a shaft mechanically coupled to the accessory gear box such that the accessory gear box is operably disposed between the shaft and the starter/generator. The turbine engine also includes a clutch operably disposed between the accessory gear box and the starter generator. The clutch is operable to slip in and out of full engagement in response to a first predetermined level of torque between the starter/generator and the accessory gear box.

Turbine engine

A multi-plate clutch is provided to couple a drive shaft from a gas turbine engine with a driven shaft of a lift fan. When disengaged the plates of the clutch can be physically separated. Plates of one shaft are coupled to the shaft with individual energy members that return the plates to a disengaged position. The plates of the other shaft can be coupled together with a travel member and/or lug key and energy devices between at least some of the plates.

Lift fan clutch

A dual clutch arrangement is disclosed herein. The dual clutch arrangement includes a first input rotatable member. The dual clutch arrangement also includes an output rotatable member. The dual clutch arrangement also includes a first clutch coupling the first input rotatable member and the output rotatable member such that the first input rotatable member drives the output rotatable member in rotation. The first clutch is operable to be overrun. The dual clutch arrangement also includes a second input rotatable member. The dual clutch arrangement also includes a second clutch operable to selectively couple the second input rotatable member and the output rotatable member such that the second input rotatable member drives the output rotatable member in rotation. The first clutch is overrun when the second clutch is engaged. The dual clutch arrangement can be one exemplary way of practicing the method of operating a turbine engine to produce thrust for a vehicle, directing air into the turbine engine with a fan during said operating step, and changing a speed of the fan during said operating step to change a bypass ratio of the turbine engine.

Dual clutch arrangement and method

A gearing arrangement is disclosed herein. The gearing arrangement includes a shaft operable to rotate about an axis of rotation. The gearing arrangement also includes a first gear fixed for rotation with the shaft and encircling the axis of rotation. The gearing arrangement also includes a plate member positioned radially adjacent to the shaft. The gearing arrangement also includes a second gear operable to mesh with the first gear. The gearing arrangement also includes a layshaft supporting the second gear. The layshaft extends along a central axis between first and second ends. The layshaft is engageable with the plate member in a plurality of different positions to adjustably position the second gear relative to the first gear.

Gearing arrangement

A material wear indication system is provided that includes a friction plate capable of engaging a moving surface and a wear indicator. The friction plate includes a wearable portion and a non-wearable portion. In one embodiment the wear indicator is embedded in the non-wearable portion and is prevented from contacting the moving surface until the wearable surface has been sufficiently eroded. When the wear indicator contacts the moving surface it emits a particulate matter that can be detected by a sensor. The sensor is operable to generate an electrical signal that is transmitted to a control unit when the wearable surface has eroded thereby exposing the wear indicator to the moving surface.

Material wear indication system

A wear indicating friction disc assembly includes at least two friction discs and may include a plurality of clamping assemblies positioned around a circumference of the friction discs to clamp at least two of the friction discs together. At least one of the clamping assemblies may include a wear indicating washer with a wear indicating portion extending into a portion of one at least one of the friction discs. A height of the wear indicating portion is set to engage the opposing friction member at a predetermined wear level of the friction disc assembly and to emit a detectable signal upon sliding engagement with the opposing friction member.

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Greenwood, IN, United States of America

Andrew D Copeland