Gas turbine engine comprising a casing surrounding a rotary assembly and a manifold secured to the casing via a securing arrangement
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/28
F02C-007/20
F02C-007/12
출원번호
UP-0137424
(2005-05-26)
등록번호
US-7857585
(2011-02-24)
우선권정보
GB-0414043.0(2004-06-23)
발명자
/ 주소
Dhaliwal, Kamaljit Kaur
출원인 / 주소
Rolls-Royce, PLC
대리인 / 주소
Oliff & Berridge, PLC
인용정보
피인용 횟수 :
2인용 특허 :
11
초록▼
A securing arrangement for securing a manifold to a casing (surrounding a rotary assembly) is disclosed the securing arrangement comprises a bracket defining a recess co-operable with a radially extending part of the casing. Securing means, provide to secure the bracket to the aforesaid radially out
A securing arrangement for securing a manifold to a casing (surrounding a rotary assembly) is disclosed the securing arrangement comprises a bracket defining a recess co-operable with a radially extending part of the casing. Securing means, provide to secure the bracket to the aforesaid radially outwardly extending part.
대표청구항▼
I claim: 1. A gas turbine engine comprising a casing surrounding a rotary assembly and a manifold secured to the casing via a securing arrangement, the manifold being configured to carry air, the securing arrangement comprising: a bracket that is separate from the casing and the manifold, wherein t
I claim: 1. A gas turbine engine comprising a casing surrounding a rotary assembly and a manifold secured to the casing via a securing arrangement, the manifold being configured to carry air, the securing arrangement comprising: a bracket that is separate from the casing and the manifold, wherein the bracket comprises two opposing wall members in a central part of the bracket, and attachment lugs at two end portions of the bracket, the bracket that includes the two opposing wall members and the attachment lugs is a one-piece member, and the two opposing wall members define a recess; a radially outwardly extending part of the casing located between the wall members of the bracket; a securing unit that extends through the wall members of the bracket and the radially outwardly extending part of the casing; and fasteners that fasten the attachment lugs of the bracket to the manifold; wherein: the bracket is located between the manifold and the casing, and the bracket is secured to the casing through the wall members at the central part of the bracket and is secured to the manifold through the attachment lugs at both end portions of the bracket, and the manifold comprises an inner wall that faces the bracket, the inner wall has a configuration corresponding to a configuration of the bracket including the two opposite wall members, and the inner wall has a plurality of apertures through which the air is configured to flow and impinge on the casing including the radially outwardly extending part. 2. The gas turbine engine according to claim 1, wherein the securing means comprises an insertion means insertable into the radially outwardly extended part of the casing. 3. The gas turbine engine according to claim 2, wherein the insertion means comprise an insertion member. 4. The gas turbine engine according to claim 3, wherein the insertion member is insertable into an aperture in the radially outwardly extending part of the casing. 5. The gas turbine engine according to claim 3, wherein the insertion means further comprise a bush having an aperture into which the insertion member can be inserted. 6. The gas turbine engine according to claim 5, wherein the bush is insertable into the radially outwardly extending part of the casing. 7. The gas turbine engine according to claim 5, wherein the bush defines an aperture into which the insertion member can be inserted. 8. The gas turbine engine according to claim 3, wherein the bracket is of a W shaped configuration, and comprises an upstanding portion, to define the recess. 9. The gas turbine engine according to claim 8, wherein the upstanding portion is centrally provided on the bracket, and the upstanding portion comprises the opposed wall members. 10. The gas turbine engine according to claim 8, wherein the upstanding portion defines an aperture for the insertion member. 11. The gas turbine engine according to claim 10, wherein the aperture is a slot which has a longitudinal axis which is generally parallel to the circumference of the manifold. 12. The gas turbine engine according to claim 11, wherein the slot is provided in the upstanding portion to allow circumferential movement of the bracket on expansion of the casing. 13. The gas turbine engine according to claim 11, wherein the upstanding portion comprises opposed wall members, and a slot is provided in each wall member. 14. The gas turbine engine according to claim 13, wherein the slots are aligned with each other. 15. The gas turbine engine according to claim 3, wherein protection means is provided between the bracket and the radially outwardly extending part of the casing. 16. The gas turbine engine according to claim 15, wherein the protection means defines an aperture through which the insertion member can be inserted. 17. The gas turbine engine according to claim 15, wherein the protection means comprises an anti-fret liner to prevent wear of one or both of the bracket and the manifold. 18. The gas turbine engine according to claim 1, wherein each fastener comprises a bolt, and the end portions define an aperture for receipt of the bolt. 19. A manifold assembly comprising a manifold and a securing arrangement as claimed in claim 1 for securing the manifold to a casing of a rotary assembly. 20. A manifold assembly according to claim 19, wherein the manifold is generally annular in configuration. 21. A manifold assembly according to claim 19, wherein the manifold comprises an inlet member to allow fluid to enter the manifold, the inlet member comprising an entrance face which is non-parallel to a main axis of the manifold. 22. A manifold assembly comprising a manifold having a main axis and a securing arrangement as claimed in claim 1 for securing the manifold to a casing on a rotary component, wherein the manifold comprises an inlet member to allow fluid to enter the manifold, the inlet member having an entrance face which is non-parallel to the main axis of the manifold. 23. A manifold assembly according to claim 22, wherein the securing arrangement includes a bracket defining a recess co-operable with a radially outwardly extending part of the casing, and securing means for securing the bracket to the aforesaid radially outwardly extending part. 24. A rotary assembly incorporating a manifold assembly according to claim 23. 25. A gas turbine engine incorporating a rotary assembly as claimed in claim 24. 26. A gas turbine engine according to claim 25 wherein the rotary assembly comprises a turbine.
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이 특허에 인용된 특허 (11)
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