Bearing outer race retention during high load events
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/04
F02C-007/06
F16C-019/16
F16C-035/067
F16C-035/04
F16C-033/58
출원번호
US-0017805
(2016-02-08)
등록번호
US-10196980
(2019-02-05)
발명자
/ 주소
Ganiger, Ravindra Shankar
Carter, Bruce Alan
Corman, Charles Andrew
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight
A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. A plurality of edge recesses are defined in the bearing housing and a plurality of lug tabs extending radially from the engine's interface shell limit are disposed in the edge recess to limit the deflection and self-arrest the distortion of the retention housing. A gas turbine engine includes the retention housing described above.
대표청구항▼
1. A retention housing for the outer race of a ball bearing for a high pressure spool of a gas turbine engine, the axial spool defining an axis of rotation, the engine having an interface shell configured to engage the retention housing to restrain axial movement of the retention housing, the retent
1. A retention housing for the outer race of a ball bearing for a high pressure spool of a gas turbine engine, the axial spool defining an axis of rotation, the engine having an interface shell configured to engage the retention housing to restrain axial movement of the retention housing, the retention housing comprising: a ball bearing housing defining a cylindrical inner surface that is disposed equidistantly from an axis of rotation that extends in an axial direction, a radial direction being defined in a direction that is normal to the axial direction, the ball bearing housing defining a forward end disposed axially spaced apart from an aft end;a spring finger housing disposed radially apart from and radially outwardly from the ball bearing housing and disposed concentrically around the ball bearing housing, the spring finger housing defining a forward end disposed axially spaced apart from an aft end, the forward end of the spring finger housing being connected to the forward end of the ball bearing housing;the spring finger housing defining a plurality of axially extending fingers, each finger defining a forward end and an aft end disposed axially spaced apart from and opposite to the forward end of each respective finger, each finger being spaced circumferentially apart from each nearest adjacent finger, the plurality of forward ends of the fingers forming a monolithic structure with the spring finger housing, and the plurality of aft ends of the fingers forming a monolithic structure with the spring finger housing;the aft end of the ball bearing housing defining a plurality of edge recesses, each edge recess being defined by a depth extending in the radial direction away from the spring finger housing and extending in the aft direction away from the forward end of the ball bearing housing; andwherein the gas turbine engine, further comprises a plurality of lug tabs, a respective one of the plurality of lug tabs being disposed in a respective one of the plurality of edge recesses, each lug tab has one end that is disposed at least partially within the respective edge recess and an opposite end projecting radially from the interface shell. 2. The retention housing of claim 1, wherein the depth of each edge recess in the radial direction is less than the thickness of the aft end of the of the ball bearing housing. 3. The retention housing of claim 1, wherein each edge recess is configured to engage the interface shell. 4. The retention housing of claim 1, wherein each edge recess is configured to engage the interface shell in a manner so that each edge recess includes a circumferential gap between the aft end of the of the ball bearing housing and the interface shell. 5. The retention housing of claim 1, wherein a circumferential gap is on the order of 20 thousandths of an inch to 50 thousandths of an inch. 6. The retention housing of claim 1, wherein each finger includes an intermediate portion disposed between the forward end and the aft end of each finger, and the intermediate portion of each finger is tapered with respect to the forward end and the aft end of each finger. 7. The retention housing of claim 6, wherein the intermediate portion of each finger is thicker than the forward end of each finger. 8. The retention housing of claim 1, wherein the spring finger housing and the ball bearing housing are formed as a monolithic structure. 9. The retention housing of claim 1, further comprising an annular mounting flange extending radially outwardly from the aft end of the spring finger housing. 10. The retention housing of claim 1, wherein the spring finger housing and the annular mounting flange are formed as a monolithic structure. 11. A gas turbine engine, comprising: a fan including a plurality of blades extending radially from a hub and rotatable about a first axis of rotation defined centrally through the hub;a compressor disposed downstream from the fan;a turbine disposed downstream of the compressor;a rotatable input shaft mechanically coupling the compressor to rotate in unison with the turbine;an engine envelope surrounding the fan, the compressor, and the turbine; andan outer casing disposed within the engine envelope and surrounding the compressor and the turbine;a ball bearing having an inner race rotatable with respect to an outer race, wherein the inner race is non-rotatably coupled to the input shaft;an interface shell that is non-rotatably coupled to the outer casing; anda retention housing that non-rotatably couples the outer casing to the outer race of the ball bearing; andwherein the retention housing further including: a ball bearing housing defining a cylindrical inner surface that is disposed equidistantly from an axis of rotation that extends in an axial direction, a radial direction being defined in a direction that is normal to the axial direction, the ball bearing housing defining a forward end disposed axially spaced apart from an aft end;a spring finger housing disposed radially apart from and radially outwardly from the ball bearing housing and disposed concentrically around the ball bearing housing, the spring finger housing defining a forward end disposed axially spaced apart from an aft end, the forward end of the spring finger housing being connected to the forward end of the ball bearing housing,the spring finger housing defining a plurality of axially extending fingers, each finger defining a forward end and an aft end disposed axially spaced apart from and opposite to the forward end of each respective finger, each finger being spaced circumferentially apart from each nearest adjacent finger, the plurality of forward ends of the fingers forming a monolithic structure with the spring finger housing, and the plurality of aft ends of the fingers forming a monolithic structure with the spring finger housing, andthe aft end of the ball bearing housing defining a plurality of edge recesses, each edge recess extending in the radial direction and defining an open end; andwherein the gas turbine engine, further comprises a plurality of lug tabs, a respective one of the plurality of lug tabs being disposed in a respective one of the plurality of edge recesses, each lug tab has one end that is disposed at least partially within the respective edge recess and an opposite end projecting radially from the interface shell. 12. The gas turbine engine of claim 11, wherein each edge recess defines a blind end spaced apart in the radial direction from the open end. 13. The gas turbine engine of claim 11, wherein each edge recess defines a blind end spaced apart in the radial direction from the open end of each respective edge recess and disposed farther away from the spring finger housing than the disposition of the open end of each edge recess. 14. The gas turbine engine of claim 11, wherein the end of each respective lug tab that projects from the interface shell defines a free end that is spaced apart in the radial direction from the blind end of the respective edge recess and defines a radial gap between the respective free end and the respective blind end. 15. The gas turbine engine of claim 11, wherein each of the plurality of lug tabs extends radially from the interface shell, each respective one of the plurality of lug tabs being aligned with a respective one of the plurality of edge recesses to form a plurality of aligned lug tabs and edge recesses and wherein each of the plurality of lug tabs defines an exterior peripheral surface that is disposed in opposition to a radially extending wall that partially defines a respective edge recess. 16. The gas turbine engine of claim 15, wherein a circumferential gap is defined between the exterior peripheral surface of a respective one of the plurality of lug tabs and the radially extending wall that partially defines the respective edge recess. 17. The gas turbine engine of claim 15, wherein an axial gap is defined between the exterior peripheral surface of a respective one of the plurality of lug tabs and the radially extending wall that partially defines the respective edge recess.
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이 특허에 인용된 특허 (13)
Ciokajlo John J. (Cincinnati OH) Loewe Jeffre G. (Cincinnati OH), Bearing assembly for use in high temperature operating environment.
Stout, David E.; Birdi, Balwinder S.; Down, Edward M.; Meacham, Walter L., High speed aerospace generator resilient mount, combined centering spring and squeeze film damper.
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