Gear rim integrated bearing of a gearbox of a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsMichel Desjardins, Guillaume Landry-Drolet
Life of this patent
Estimating the term…
Abstract
A gearbox of a gas turbine engine of an aircraft with a two-bearing arrangement is provided. The gearbox includes a coupling shaft rotatable about a rotational axis thereof, an output gear including a first gear element, a gear web and a bearing assembly. The gear web is rotatable with the coupling shaft and includes a shaft connected with the coupling shaft, a rim including a second gear element disposed to form a gear mesh with the first gear element and a web extending from the shaft to the rim. The bearing assembly includes a fixed bearing support and a bearing element supportively disposable between the fixed bearing support and the rim of the gear web.
Claims20
A gearbox of a gas turbine engine of an aircraft with a two-bearing arrangement, the gearbox comprising:
- a coupling shaft rotatable about a rotational axis thereof;
- an output gear comprising a first gear element;
- a gear web rotatable with the coupling shaft and comprising a shaft connected with the coupling shaft, a rim comprising a second gear element disposed to form a gear mesh with the first gear element and a web extending from the shaft to the rim;
- and
- a bearing assembly comprising a fixed bearing support and a bearing element supportively disposable between the fixed bearing support and the rim of the gear web,
- wherein a center of the gear mesh and a center of the bearing element are axially aligned.
A gearbox of a gas turbine engine of an aircraft, the gearbox comprising:
- a coupling shaft rotatable about a rotational axis thereof;
- an output gear comprising a first spur gear element;
- a gear web rotatable with the coupling shaft and comprising a shaft connected with the coupling shaft, a rim comprising a second spur gear element disposed to form a gear mesh with the first spur gear element and a web extending from the shaft to the rim;
- and
- a bearing assembly comprising a fixed bearing support and a bearing element supportively disposable between the fixed bearing support and the rim of the gear web and having a center axially aligned with a center of the gear mesh,
- wherein:
- the bearing element comprises a roller bearing with an inner race supportable by the fixed bearing support and an outer race integral with the rim of the gear web.
(canceled)
(canceled)
A gearbox of a gas turbine engine of an aircraft, the gearbox comprising:
- a coupling shaft rotatable about a rotational axis thereof;
- an output gear comprising a first helical gear element;
- a gear web rotatable with the coupling shaft and comprising a shaft connected with the coupling shaft, a rim comprising a second helical gear element disposed to form a gear mesh with the first helical gear element and a web extending from the shaft to the rim;
- and
- a bearing assembly comprising a fixed bearing support and a bearing element supportively disposable between the fixed bearing support and the rim of the gear web whereby a gear load and bearing reaction are axially positioned to contain a load path within a bearing reaction circle of the bearing element,
- wherein:
- an outer race of the bearing element is integral with the rim of the gear web and is formed to define a recess having a center axially offset from the gear mesh, and
- the bearing element comprises the outer race, a roller bearing received in the recess of the outer race and having a center axially offset from the gear mesh and an inner race that is supported.
(canceled)
(canceled)
Dependencies are inferred from the claim text.