IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0715343
(2007-03-08)
|
등록번호 |
US-8122723
(2012-02-28)
|
우선권정보 |
GB-0606823.3 (2006-04-05) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
6 |
초록
▼
A fluid flow control device (26, 28) comprising a guide member (30) to guide a fluid passing through a duct (22, 24, 76), the guide member (30) being movable between first and second positions; and an urging arrangement (32) capable of providing an urging force (F1) to urge the guide member (30) tow
A fluid flow control device (26, 28) comprising a guide member (30) to guide a fluid passing through a duct (22, 24, 76), the guide member (30) being movable between first and second positions; and an urging arrangement (32) capable of providing an urging force (F1) to urge the guide member (30) towards the first position, characterised in that the urging arrangement (32) is a resilient torsion bar that is formed so as to allow the guide member (30) to be moved towards the second position by a pressure force (F2) exceeding and opposite to the urging force (F1), the pressure force (F2) being provided by a pressure difference across the guide member (30).
대표청구항
▼
1. A gas turbine engine comprising: a nozzle through which a fluid can flow, the nozzle having an outlet, anda fluid flow control device arranged on the nozzle at the outlet, the fluid flow control device comprising: a guide member to guide the fluid passing through the nozzle, the guide member bein
1. A gas turbine engine comprising: a nozzle through which a fluid can flow, the nozzle having an outlet, anda fluid flow control device arranged on the nozzle at the outlet, the fluid flow control device comprising: a guide member to guide the fluid passing through the nozzle, the guide member being movable between first and second positions; andan resilient torsion bar, the resilient torsion bar being mounted to the guide member and being pre-stressed to provide an urging force to urge the guide member towards the first position and the guide member is moved towards the second position by a pressure force exceeding and opposite to the urging force, the pressure force being provided by a pressure difference across the guide member. 2. A gas turbine engine according to claim 1 wherein the resilient torsion bar is generally annular in configuration to extend around the nozzle. 3. A gas turbine engine according to claim 2 comprising an assembly that comprises a plurality of the guide members arranged adjacent one another around the resilient torsion bar. 4. A gas turbine engine according to claim 1 wherein the resilient torsion bar comprises a plurality of resilient torsion bars arranged one after another in an annular arrangement. 5. A gas turbine engine according to claim 4 wherein each resilient torsion bar has a discrete guide member mounted thereon. 6. A gas turbine engine according to claim 1 wherein the first position of the guide member provides a minimum area condition for a fluid path, and the second position of the guide member provides a maximum area of condition for the fluid path. 7. A gas turbine engine according to claim 1 wherein the guide member comprises a tapering member tapering from a wide region adjacent the resilient torsion bar, to a narrow region spaced from the resilient torsion bar. 8. A gas turbine engine according to claim 1 wherein a securing arrangement is provided to secure the guide member to the resilient torsion bar. 9. A gas turbine engine according to claim 8 wherein the securing arrangement comprises a clamp. 10. A gas turbine engine according to claim 8 wherein the securing arrangement comprises a first clamp and a second clamp. 11. A gas turbine engine according to claim 1 further comprising: a fixing element that is provided to fix the fluid flow control device to the nozzle, the fixing element extending in an upstream direction from the resilient torsion bar fixing to the nozzle. 12. A gas turbine engine according to claim 1 wherein a first stop is provided to restrict the extent of movement of the guide member when urged towards the first position and to provide a minimum area of the nozzle, and a second stop is provided to restrict the extent of travel of the guide member when being urged towards the second position, and to provide a maximum area of the nozzle. 13. A gas turbine engine according to claim 1 wherein a damping arrangement is provided to inhibit a speed at which the guide member moves between the first and second positions. 14. A gas turbine engine according to claim 1 wherein the resilient torsion bar comprises a Shape Memory Material. 15. A gas turbine engine according to claim 1 comprising an assembly that comprises fixed and moveable guide members. 16. A gas turbine engine fluid flow control according to claim 15 wherein the fixed and moveable guide members are alternately spaced apart. 17. A gas turbine engine according to claim 15 wherein the guide members have lateral edges that are angled to abut one another to provide positive location in the first or second position. 18. A gas turbine engine according to claim 1 further comprising a plurality of guide members arranged circumferentially around the outlet of the nozzle, each guide member being mounted on a common resilient torsion bar, the common resilient torsion bar extending around the nozzle. 19. A gas turbine engine according to claim 1 comprising a plurality of guide members arranged adjacent one another around the resilient torsion bar, the nozzle arrangement comprising a plurality of discrete guide members arranged on respective discrete resilient torsion bars. 20. A gas turbine engine according to claim 19 wherein the plurality of discrete guide members and the respective discrete resilient torsion bars are circumferentially arranged adjacent one another. 21. A gas turbine engine comprising a fan for directing a first flow of air through a first nozzle, and a turbine arrangement for directing a second flow of air through a second nozzle, a first fluid flow control device as claimed in claim 1 provided on the first nozzle, and a second fluid flow control device as claimed in claim 1 provided on the second nozzle. 22. A gas turbine engine comprising: a nozzle that has an outlet;a fluid flow control device arranged on the nozzle at the outlet; the fluid flow control device comprising: a guide member to guide the fluid passing through the nozzle, the guide member being movable between first and second positions; and a resilient torsion bar that is mounted to the nozzle, the resilient torsion bar being pre-stressed to provide an urging force to urge the guide member towards the first position, wherein the guide member is moved towards the second position by a pressure force exceeding and opposite to the urging force, the pressure force being provided by a pressure difference across the guide member. 23. A gas turbine engine according to claim 1, further comprising: a clamping arrangement, wherein the guide member being mounted to the resilient torsion bar with the clamping arrangement. 24. A gas turbine engine according to claim 1, further comprising: a plurality of guide members that are circumferentially mounted on the resilient torsion bar. 25. A gas turbine engine according to claim 22, further comprising: a clamping arrangement, wherein the guide member being mounted to the resilient torsion bar with the clamping arrangement. 26. A gas turbine engine according to claim 22, further comprising: a plurality of guide members that are circumferentially mounted on the resilient torsion bar.
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