Annular spring for a bearing assembly of a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/06
F16F-001/02
F16C-027/04
F16C-035/077
F16C-019/26
출원번호
US-0626659
(2015-02-19)
등록번호
US-9850814
(2017-12-26)
발명자
/ 주소
Grogg, Gary L.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
O'Shea Getz P.C.
인용정보
피인용 횟수 :
0인용 특허 :
42
초록
An annular spring for a bearing assembly of gas turbine engine is provided. The annular spring includes a multiple of ligaments between an inner support and an outer support.
대표청구항▼
1. An assembly for a bearing assembly of gas turbine engine, the assembly comprising: an annular first spring;an annular second spring comprising an inner support;an outer support; anda multiple of ligaments between the inner support and the outer support, a first of the ligaments including a first
1. An assembly for a bearing assembly of gas turbine engine, the assembly comprising: an annular first spring;an annular second spring comprising an inner support;an outer support; anda multiple of ligaments between the inner support and the outer support, a first of the ligaments including a first end segment, a second end segment and an intermediate segment extending circumferentially between the first end segment and the second end segment;wherein the first end segment projects substantially radially out from the inner support, the second end segment projects substantially radially in from the outer support, and the first of the ligaments has an overall circumferential width defined between an outside surface of the first end segment and an outside surface of the second end segment; andan oil film damper comprising a first flange, a second flange and a center portion axially between and projecting radially outward from the first flange and the second flange, the center portion axially between the first spring and the second spring, wherein the first spring is supported by the first flange, and the second spring is supported by the second flange. 2. assembly as recited in claim 1, wherein each of the multiple of ligaments are serpentine shaped. 3. The assembly as recited in claim 1, wherein each of the multiple of ligaments includes a radial flat. 4. The assembly as recited in claim 1, wherein each of the multiple of ligaments is radiused. 5. The assembly as recited in claim 1, wherein the annular first spring is additively manufactured. 6. A bearing compartment for a gas turbine engine, comprising: a bearing support static structure;a bearing assembly radially inboard of the bearing support static structure;an oil film damper radially between the bearing assembly and the bearing support static structure;an annular first spring radially between the bearing assembly and the bearing support static structure; andan annular second spring radially between the bearing assembly and the bearing support static structure, the second spring including a multiple of ligaments, an inner support ring and an outer support ring;wherein a first of the multiple of ligaments is configured to form a first indentation and a second indentation, the first indentation extends radially inward to a first indentation end defined by the first of the multiple of ligaments, and the second indentation extends radially outward to a second indentation end defined by the first of the multiple of ligaments;wherein the first of the multiple of ligaments consists of a first end segment, a second end segment and an intermediate segment disposed circumferentially between the first end segment and the second end segment;wherein the second end segment projects substantially radially in from the outer support ring, and partially defines the first indentation;wherein the first end segment projects substantially radially out from the inner support ring, and partially defines the second indentation;wherein the oil film damper comprises a first flange, a second flange and a center portion projecting radially outward from the first flange and the second flange;wherein the center portion is disposed axially between the annular first spring and the annular second spring;wherein the annular first spring is supported by the first flange; andwherein the annular second spring is supported by the second flange. 7. The bearing compartment as recited in claim 6, wherein each of the multiple of ligaments are serpentine shaped and are circumferentially distributed. 8. The bearing compartment as recited in claim 6, wherein the inner support ring is supported upon the oil film damper. 9. The bearing compartment as recited in claim 6, wherein the outer support ring is supported upon the bearing support static structure. 10. The bearing compartment as recited in claim 6, further comprising an engine shaft, wherein the bearing assembly supports the engine shaft. 11. The bearing compartment as recited in claim 6, further comprising a retaining ring that retains the oil film damper to an outer race of the bearing assembly. 12. The bearing compartment as recited in claim 6, wherein each of the multiple of ligaments has an axial length that is less than an axial length of the bearing assembly. 13. The bearing compartment as recited in claim 6, wherein the first of the multiple of ligaments has a generally S-shaped sectional geometry. 14. A method, comprising: locating an annular first spring radially between an oil film damper and a bearing support static structure, the first spring including a multiple of ligaments, an inner support and an outer support; andlocating an annular second spring radially between the oil film damper and the bearing support static structure, a center portion of the oil film damper axially separating the annular first spring from the annular second spring;wherein a first of the multiple of ligaments is configured with a first recess and a second recess, the first recess has a first open end and a first closed end formed by a first surface of the first of the multiple of ligaments, the first recess extends radially inward from the first open end to the first closed end, the second recess has a second open end and a second closed end formed by a second surface of the first of the multiple of ligaments, and the second recess extends radially outward from the second open end to the second closed end;wherein the first of the multiple of ligaments consists of a first end segment, a second end segment and an intermediate segment completely circumferentially between the first end segment and the second end segment;wherein the second end segment projects substantially radially in from the outer support, and partially defines the first recess;wherein the first end segment projects substantially radially out from the inner support, and partially defines the second recess;wherein the oil film damper comprises a first flange, a second flange and the center portion which projects radially outward from the first flange and the second flange;wherein the center portion is axially between the annular first spring and the annular second spring;wherein the annular first spring is supported by the first flange; andwherein the annular second spring is supported by the second flange. 15. The method as recited in claim 14, further comprising radially orienting the multiple of ligaments. 16. The method as recited in claim 14, wherein the multiple of ligaments are oriented in a serpentine. 17. The method as recited in claim 14, wherein the multiple of ligaments each have an axial length that is less than an axial length of the oil film damper. 18. The method as recited in claim 14, wherein the first spring and the second spring flank the oil film damper.
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