Gas turbine engine geared architecture axial retention arrangement
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-015/12
F03D-011/02
A47C-007/74
B63H-001/00
F16H-057/04
출원번호
US-0435353
(2012-03-30)
등록번호
US-8790075
(2014-07-29)
발명자
/ 주소
Coffin, James B.
Pescosolido, Alessio
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
2인용 특허 :
9
초록▼
A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members a
A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.
대표청구항▼
1. A support assembly for a geared architecture comprising: an engine static structure;a flex support secured to the engine static structure and including a bellow;a support structure operatively secured to the flex support;the geared architecture mounted to the support structure; andfirst members r
1. A support assembly for a geared architecture comprising: an engine static structure;a flex support secured to the engine static structure and including a bellow;a support structure operatively secured to the flex support;the geared architecture mounted to the support structure; andfirst members removably secured to one of the engine static structure and the flex support, and second members removably secured to the support structure, the first and second members circumferentially aligned with one another and spaced apart from one another during a normal operating condition, and the first and second members configured to be engageable with one another during an extreme event to limit movement of the geared architecture relative to the engine static structure in at least an axial direction away from the flex support. 2. The support assembly according to claim 1, wherein the flex support includes an end opposite the bellow, the first members removably secured to the end. 3. The support assembly according to claim 2, wherein the end is an annular mounting flange. 4. The support assembly according to claim 1, wherein the support structure includes a torque frame and a carrier, the second members are removably secured to at least one of the torque frame and the carrier. 5. The support assembly according to claim 4, wherein the support structure includes a lubrication manifold, the second members removably secured to the carrier and the lubrication manifold. 6. The support assembly according to claim 5, wherein the lubrication manifold is arranged axially between the carrier and the second members. 7. The support assembly according to claim 1, comprising threaded fasteners removably securing the first members and the second members to the flex support and the support structure, respectively. 8. A method of retrofitting a support assembly to a gas turbine engine having a geared architecture, comprising the steps of: providing attachment features in first and second structures;securing first and second members respectively to the first and second structures;arranging the first and second members in axially spaced relation to one another in an installed condition; andinstalling the first structure onto an engine static structure and installing the geared architecture onto the second structure from a first position in a first axial direction toward the second structure, wherein the first and second members are configured to cooperate to limit movement of the geared architecture relative to the second structure in at least a second axial direction opposite the first direction, wherein the first structure is a flex support having a bellow and an annular mounting flange is arranged opposite the bellow. 9. The method according to claim 8, wherein the attachment features providing step includes providing machined surfaces on the first and second structures. 10. The method according to claim 9, wherein the securing step includes mounting the first members to the annular mounting flange. 11. The method according to claim 10, wherein the securing step includes mounting a lubrication manifold onto the second structure, and securing the second members over the lubrication manifold. 12. The method according to claim 11, wherein the installing step includes securing a torque frame to the flex support and a carrier, the carrier supporting the geared architecture. 13. The method according to claim 8, wherein the arranging step includes positioning the first and second members in a first angular position relative to one another, and rotating the first and second members from the first angular position to a second angular position. 14. The method according to claim 8, wherein the securing steps include tightening threaded fasteners. 15. The method according to claim 14, wherein the securing step relating to the second members includes selecting fasteners having a length longer than a length of pre-existing fasteners at the attachment features, which are removed during retrofitting. 16. A gas turbine engine comprising: an engine static structure;a flex support secured to the engine static structure and including a bellow;a support structure operatively secured to the flex support;a geared architecture mounted to the support structure;a fan section operatively coupled to the geared architecture; andfirst members removably secured to one of the engine static structure and the flex support, and second members removably secured to the support structure, the first and second members circumferentially aligned with one another and spaced apart from one another during a normal operating condition, and the first and second members configured to be engageable with one another during an extreme fan section event to limit axial movement of the geared architecture relative to the engine static structure in at least a direction toward the fan section. 17. The gas turbine engine according to claim 16, comprising low and high spools, low pressure compressor and turbine sections mounted on the low spool, and high pressure compressor and turbine sections mounted on the high spools, the low spool operatively coupled to the geared architecture. 18. The gas turbine engine according to claim 16, wherein the geared architecture is a planetary gear train. 19. The gas turbine engine according to claim 16, wherein the fan section includes a fan shaft supporting a fan, the fan shaft supported relative to the engine static structure by bearings. 20. The gas turbine engine according to claim 16, comprising threaded fasteners removably securing the first member and the second member to the flex support and the support structure, respectively. 21. The method according to claim 8, wherein the first axial direction is an axial direction from a forward location toward a rearward location relative to the gas turbine engine. 22. The support assembly according to claim 5, wherein the lubrication manifold is annular. 23. The support assembly according to claim 6, wherein the lubrication manifold engages both the carrier and the second members. 24. The method according to claim 9, wherein the machined surfaces on the first and second structures respectively receive the first and second members in the securing step. 25. The method according to claim 11, wherein the second members engages the lubrication manifold and the second structure. 26. The method according to claim 8, wherein the first and second members are in axially interleaved spaced relation to one another in the installed condition. 27. The method according to claim 13, wherein the first and second members are in a non-interleaved relationship in the first angular position, and the first and second members are in an interleaved relationship in the second angular position. 28. The method according to claim 27, wherein the first and second members are configured to be engageable with one another during an extreme event to limit movement of the geared architecture relative to the engine static structure in a radial direction. 29. The method of claim 8, wherein the first and second members are configured to cooperate to limit movement of the geared architecture relative to the second structure in a third direction normal to the first axial direction. 30. A support assembly for a geared architecture comprising: an engine static structure;a flex support secured to the engine static structure;a support structure operatively secured to the flex support;the geared architecture mounted to the support structure; andfirst members secured to one of the engine static structure and the flex support, and second members secured to the support structure, the first and second members circumferentially aligned with one another and spaced apart from one another during a normal operating condition, and the first and second members configured to be engageable with one another during an extreme event to limit movement of the geared architecture relative to the engine static structure in at least an axial direction away from the flex support.
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이 특허에 인용된 특허 (9)
Madge, James H.; Do, Khanh Khac, Apparatus for restraining axial movement of a ring gear in a gearbox for a wind turbine.
Miller, Brandon Wayne; Vondrell, Randy M.; Bradley, Donald Albert; Ertas, Bugra Han, Systems and methods for a gas turbine engine with combined multi-directional gearbox deflection limiters and dampers.
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