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US 2026/0309090 A1Published application
Double offset reduction gearbox with motor drive for turboprop
AssigneePratt & Whitney Canada Corp.
InventorsEric S. Durocher, Paul Weaver, Roberto Brito, Bruno Chatelois
Life of this patent
Estimating the term…
Abstract
A motorized gear system of a gas turbine engine, having: a reduction gear including: an input shaft, driven by an engine output shaft; a first branch having a first shaft and a first gearset, driven by the input shaft; a second branch having a second shaft and a second gearset, driven by the input shaft; an output shaft, driven by the first branch and the second branch; and wherein the motorized gear system includes a first motor, coupled to the first branch.
Claims20
A motorized gear system of a gas turbine engine, comprising:
- a double reduction offset gear including:
- an input shaft, driven by an engine output shaft;
- a first branch having a first shaft and a first gearset, driven by the input shaft;
- a second branch having a second shaft and a second gearset, driven by the input shaft;
- an output shaft, driven by the first branch and the second branch;
- and
- wherein the motorized gear system includes a first motor, coupled to the first branch,
- wherein:
- the input shaft extends from a forward end to an aft end, and a first gear mesh is formed on a first portion of the input shaft, the first portion of the input shaft having a first diameter;
- the first shaft of the first branch extends from a forward end to an aft end, and the first gearset includes a second gear mesh formed on a first portion of the first branch having a second diameter that is larger than the first diameter, wherein the second gear mesh engages the first gear mesh;
- the first branch has a second portion that is forward of the first portion of the first branch, and the first gearset includes a third gear mesh formed on the second portion of the first branch, wherein the second portion of the first branch has a third diameter that is smaller than the second diameter;
- and
- the output shaft extends from a forward end to an aft end, and a fourth gear mesh is formed on a first portion of the output shaft having a fourth diameter that is larger than the second diameter, wherein the fourth gear mesh engages the third gear mesh;
- the input shaft has an input flange on the aft end of the input shaft and the output shaft has an output flange on the forward end of the output shaft;
- and
- the forward end of the first shaft of the first branch has a motor spline that engages the first motor.
13 more elements
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A gas turbine engine, comprising:
- an engine core;
- an engine output shaft, driven by the engine core;
- a motorized gear system including a double reduction offset gear, coupled to the engine output shaft,
- wherein the double reduction offset gear includes:
- an input shaft, driven by the engine output shaft;
- a first branch having a first shaft and a first gearset, driven by the input shaft;
- a second branch having a second shaft and a second gearset, driven by the input shaft;
- an output shaft, driven by the first branch and the second branch;
- and
- wherein the motorized gear system includes a first motor, coupled to the first branch, and
- a bladed rotor, driven by the output shaft,
- wherein:
- the input shaft extends from a forward end to an aft end, wherein the aft end is coupled to the engine output shaft, and a first gear mesh is formed on a first portion of the input shaft, the first portion of the input shaft having a first diameter;
- the first shaft of the first branch extends from a forward end to an aft end, and the first gearset includes a second gear mesh formed on a first portion of the first branch having a second diameter that is larger than the first diameter, wherein the second gear mesh engages the first gear mesh;
- the first branch has a second portion that is forward of the first portion of the first branch, and the first gearset includes a third gear mesh formed on the second portion of the first branch, wherein the second portion of the first branch has a third diameter that is smaller than the second diameter;
- and
- the output shaft extends from a forward end to an aft end, and a fourth gear mesh is formed on a first portion of the output shaft having a fourth diameter that is larger than the second diameter, wherein the fourth gear mesh engages the third gear mesh;
- the input shaft has an input flange on the aft end of the input shaft to connect with the engine output shaft and the output shaft has an output flange on the forward end of the output shaft to connect with a rotor blade;
- and
- the forward end of the first shaft of the first branch has a motor spline that engages the first motor.
17 more elements
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A method of operating a gas turbine engine comprising:
- driving a bladed-rotor via a reduction gear of a motorized gear system, the reduction gear having an input shaft that is driven by an engine output shaft of the gas turbine engine, a first branch that is driven by the input shaft, a second branch that is driven by the input shaft, an output shaft that is driven by the first branch and the second branch, and the motorized gear system including a first motor coupled to the first branch, and
- selectively controlling the first motor to operate in a motor mode and provide supplemental power to drive the bladed-rotor.
Dependencies are inferred from the claim text.