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US 12,459,660 B1Granted
Limited slip torque-limiter coupling
AssigneeROLLS-ROYCE plc
InventorAndrew D. Copeland
Life of this patent
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Abstract
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.
Claims19
An aircraft comprising
- a first propulsion unit including a first drive system configured to output rotational motion and a first driven rotor coupled to the first drive system and configured to accelerate air providing thrust to move the aircraft,
- a second propulsion unit including a second drive system configured to output rotational motion and a second driven rotor coupled to the second drive system and configured to accelerate air providing thrust to move the aircraft, and
- a controller coupled to both the first propulsion unit and the second propulsion unit, the 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 or the second propulsion unit to maintain a desired overall level of thrust delivery from a combination of the first propulsion unit and the second propulsion unit,
- wherein each of the first propulsion unit and the second propulsion unit include a gas turbine engine with a drive shaft, an output shaft coupled between the drive shaft and the respective driven rotor, and a mechanical means for decoupling the output shaft from the drive shaft in response to a transmitted torque passing between the drive shaft and the output shaft exceeding a predetermined limit and for recoupling the output shaft to the drive shaft upon return of the transmitted torque to less than the predetermined limit without reliance on electronic controls so as to quickly avoid over-torque conditions that can damage propulsion unit systems,
- wherein the mechanical means includes a first portion coupled to the output shaft, a second portion coupled to the drive shaft, and a bolt configured to couple the first portion to the second portion, wherein the bolt is configured to adjust the predetermined limit.
2 more elements
An aircraft comprising
- a first propulsion unit including a first drive system configured to output rotational motion and a first driven rotor coupled to the first drive system and configured to accelerate air providing thrust to move the aircraft,
- a second propulsion unit including a second drive system configured to output rotational motion and a second driven rotor coupled to the second drive system and configured to accelerate air providing thrust to move the aircraft, and
- a controller coupled to both the first propulsion unit and the second propulsion unit, the 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 or the second propulsion unit to maintain a desired overall level of thrust delivery from a combination of the first propulsion unit and the second propulsion unit,
- wherein each of the first propulsion unit and the second propulsion unit include a gas turbine engine with a drive shaft, an output shaft coupled between the drive shaft and the respective driven rotor, and a limited-slip coupler having a first portion coupled to the output shaft and a second portion coupled to the drive shaft, the limited-slip coupler to decouple the output shaft from the drive shaft in response to a transmitted torque passing between the drive shaft and the output shaft exceeding a predetermined limit and for recoupling the output shaft to the drive shaft upon return of the transmitted torque to less than the predetermined limit,
- wherein the limited-slip coupler includes a central bolt aligned with the drive shaft and the output shaft, the bolt configured to adjust the predetermined limit.
2 more elements
An aircraft comprising
- a first propulsion unit,
- a second propulsion unit, and
- a controller coupled to both the first propulsion unit and the second propulsion unit, the 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 or the second propulsion unit to maintain a desired overall level of thrust delivery from a combination of the first propulsion unit and the second propulsion unit,
- wherein each of the first propulsion unit and the second propulsion unit include a gas turbine engine with a drive shaft, an output shaft coupled between the drive shaft and a respective driven rotor, and a limited-slip coupler having a first portion coupled to the output shaft and a second portion coupled to the drive shaft, the limited-slip coupler to decouple the output shaft from the drive shaft in response to a transmitted torque passing between the drive shaft and the output shaft exceeding a predetermined limit and for recoupling the output shaft to the drive shaft upon return of the transmitted torque to less than the predetermined limit,
- wherein the limited-slip coupler includes a central bolt aligned with the drive shaft and the output shaft, the bolt configured to adjust the predetermined limit to set the predetermined limit within a maximum torque limit of the output shaft.
2 more elements
Dependencies are inferred from the claim text.