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US 12,560,100 B1Granted
Double directionally pre-loaded damped ball bearing
AssigneePratt & Whitney Canada Corp.
InventorIan Macfarlane
Life of this patent
Estimating the term…
Abstract
A gas turbine engine of an aircraft is provided. The gas turbine engine includes a shaft, a housing and an auxiliary ball bearing assembly to rotatably support the shaft within the housing. The auxiliary ball bearing assembly includes inner and outer races, ball bearings between the inner and outer races, an axial spring anchored between the housing and the outer race to prevent axial movement of the shaft during overhaul and an oil cavity defined between the housing and the outer race for axial damping during the overhaul and for radial damping during operational conditions.
Claims20
A gas turbine engine of an aircraft, comprising:
- a shaft;
- a housing;
- and
- an auxiliary ball bearing assembly to rotatably support the shaft within the housing and comprising:
- inner and outer races;
- ball bearings between the inner and outer races;
- an axial spring anchored between the housing and the outer race to prevent axial movement of the shaft during overhaul;
- and
- an oil cavity having a first cavity portion with a forward side and a second cavity portion with an aft side, the aft side of the second cavity portion being fluidly communicative with the forward side of the first cavity portion,
- the first cavity portion being defined between the second flange and a forward portion of the first axial member of the housing and the second radial face and an aft portion of the axial section of the outer race, and
- the second cavity portion being defined between the second axial members of the housing and a forward portion of the axial section of the outer race.
8 more elements
A gas turbine engine of an aircraft, comprising:
- a shaft;
- a housing comprising first, second and third flanges, a first axial member and a second axial member;
- and
- an auxiliary ball bearing assembly to rotatably support the shaft within the housing and comprising:
- an inner race;
- an outer race comprising an outboard section having first and second radial faces, an inboard section having a third radial face and an axial section between the outboard section and the inboard section;
- ball bearings between the inner and outer races;
- first and second axial springs anchored between the first flange and the first radial face and between the third flange and the third radial face, respectively;
- and
- an oil cavity having a first cavity portion with a forward side and a second cavity portion with an aft side, the aft side of the second cavity portion being fluidly communicative with the forward side of the first cavity portion,
- the first cavity portion being defined between the second flange and a forward portion of the first axial member of the housing and the second radial face and an aft portion of the axial section of the outer race, and
- the second cavity portion being defined between the second axial members of the housing and a forward portion of the axial section of the outer race.
9 more elements
A gas turbine engine of an aircraft, comprising:
- a shaft;
- a housing comprising first and second flanges, a first axial member and a second axial member;
- and
- an auxiliary ball bearing assembly to rotatably support the shaft within the housing and comprising:
- an inner race;
- an outer race comprising an outboard section having first and second radial faces, an inboard section and an axial section between the outboard section and the inboard section;
- ball bearings between the inner and outer races;
- an axial spring anchored between the first flange and the first radial face;
- and
- an oil cavity having a first cavity portion with a forward side and a second cavity portion with an aft side, the aft side of the second cavity portion being fluidly communicative with the forward side of the first cavity portion,
- the first cavity portion being defined between the second flange and a forward portion of the first axial member of the housing and the second radial face and an aft portion of the axial section of the outer race, and
- the second cavity portion being defined between and the second axial members of the housing and a forward portion of the axial section of the outer race.
9 more elements
Dependencies are inferred from the claim text.