Epicyclic system with bevel attachment for dual-power applications
AssigneePratt & Whitney Canada Corp.
InventorRoberto Brito
Life of this patent
Estimating the term…
Abstract
A reduction gearbox of an aircraft propulsion system includes an input shaft configured to input rotational energy into the reduction gearbox, an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system, and an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft. A transfer gear is positioned at a component of the epicyclic gear arrangement and is configured to mechanically couple an accessory component to the reduction gearbox.
Claims12
A reduction gearbox of an aircraft propulsion system, comprising:
- an input shaft configured to input rotational energy into the reduction gearbox;
- an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system;
- an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft;
- a transfer gear disposed at a component of the epicyclic gear arrangement and configured to mechanically couple an accessory component to the reduction gearbox;
- wherein the transfer gear is a bevel gear disposed at one of a planet carrier or a ring gear of the epicyclic gear arrangement, the transfer gear configured to be coupled directly to a corresponding component bevel gear of an accessory gear train of the accessory component.
A reduction gearbox and accessory component arrangement of an aircraft propulsion system, comprising:
- a reduction gearbox including:
- an input shaft configured to input rotational energy into the reduction gearbox;
- an output shaft configured to output rotational energy from the reduction gearbox to a propulsor of the aircraft propulsion system;
- an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft;
- and
- a transfer gear disposed at a component of the epicyclic gear arrangement;
- and
- an accessory component mechanically coupled to the epicyclic gear arrangement via the transfer gear to transmit rotational energy between the reduction gearbox and the accessory component;
- wherein the transfer gear is a bevel gear disposed at one of a planet carrier or a ring gear of the epicyclic gear arrangement, the transfer gear configured to be coupled directly to a corresponding component bevel gear of an accessory gear train of the accessory component.
A propulsion system of an aircraft, comprising:
- an engine configured to provide rotational energy to a reduction gearbox, the reduction gearbox including:
- an input shaft configured to input rotational energy into the reduction gearbox;
- an output shaft configured to output rotational energy from the reduction gearbox;
- an epicyclic gear arrangement mechanically coupling the output shaft to the input shaft;
- and
- a transfer gear disposed at a component of the epicyclic gear arrangement;
- an accessory component mechanically coupled to the epicyclic gear arrangement via the transfer gear to transmit rotational energy between the reduction gearbox and the accessory component;
- and
- a propulsor operably connected to the output shaft and driven by rotation of the output shaft;
- wherein the transfer gear is a bevel gear disposed at one of a planet carrier or a ring gear of the epicyclic gear arrangement, the transfer gear configured to be coupled directly to a corresponding component bevel gear of an accessory gear train of the accessory component.
Dependencies are inferred from the claim text.