[특허]Recessable damper for turbine

Rolls-Royce North American Technologies Inc.

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특허 상세정보

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Recessable damper for turbine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/06 F01D-005/22
출원번호	US-0552089 (2014-11-24)
등록번호	US-9797270 (2017-10-24)
발명자 / 주소	O'Leary, Mark
출원인 / 주소	Rolls-Royce North American Technologies Inc.
대리인 / 주소	Barnes & Thornburg LLP
인용정보	피인용 횟수 : 0 인용 특허 : 19

초록

A turbine blade damping system for a turbine includes a turbine blade platform and a damper recessable within a pocket defined by the platform. An underside of the platform defines a beveled surface. An outer side of the damper defines a complementary beveled surface. When the turbine spools up, centrifugal force acting on the damper forces it in an outward direction from the pocket toward a mating surface of an adjacent turbine blade platform.

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1. A turbine blade damper system comprising a platform having a leading end, a trailing end, a first circumferential side, a second circumferential side, a radially-outward side, and a radially-inward side, the radially-inward side defining a pocket extending circumferentially inwardly from the first circumferential side, the pocket having a ceiling portion, a first wall portion extending radially inward from the ceiling portion proximate the leading end, a second wall portion extending radially inward from the ceiling portion proximate the trailing end, a first floor portion extending from the first wall portion toward the second wall portion, and a second floor portion extending from the second wall portion toward the first wall portion, the ceiling portion defining a pocket beveled surface extending circumferentially inwardly from the first circumferential side, and the second circumferential side defining a platform sealing surface; anda damper having a leading end, a trailing end, a first circumferential side, a second circumferential side, a body portion, a radially-outward side, a first leg portion extending radially inwardly from the leading end of the body portion, a second leg portion extending radially inwardly from the trailing end of the body portion, the first circumferential side defining a damper sealing surface, the radially-outward side defining a damper beveled surface;the damper beveled surface slidingly engaged with the pocket beveled surface, and the damper movable with respect to the platform between a first position wherein at least a portion of the damper is recessed within the pocket and a second position wherein a lesser portion of the damper is recessed within the pocket and the damper sealing surface is engaged with a platform sealing surface of an adjacent platform, wherein the first and second leg portions of the damper define respectively a first outer surface and a second outer surface, wherein the first outer surface and the second outer surface are in sliding engagement with the first and second wall portions of the pocket, wherein the first and second leg portions of the damper define respectively a first foot and a second foot, wherein the first foot and the second foot are respectively engaged with the first and second floor portions when the damper is in the first position, and further comprising a first lip extending radially outwardly from the first floor portion proximate a free end of the first foot and a second lip extending radially outwardly from the second floor portion proximate a free end of the second foot. 2. The turbine blade damping system of claim 1, further comprising an airfoil extending radially outwardly from the radially-outward side of the platform. 3. The turbine blade damping system of claim 2, further comprising a root extending radially inwardly from the radially-inward side of the platform. 4. The turbine blade damping system of claim 1, further comprising an adjacent platform, the damper selectively engagable with the adjacent platform. 5. The turbine blade damping system of claim 4, the platform and the adjacent platform attached to a wheel. 6. The turbine blade damping system of claim 1, wherein the body portion and the first leg of the damper cooperate to define the damper sealing surface. 7. The turbine blade damping system of claim 1, wherein the body portion, the first leg, and the second leg of the damper cooperate to define the damper sealing surface. 8. A turbine blade damper system comprising a plurality of platforms, each platform having a leading end, a trailing end, a first circumferential side, a second circumferential side, a radially-outward side, and a radially-inward side, the radially-inward side defining a pocket extending circumferentially inwardly from the first circumferential side, the pocket having a ceiling portion, a first wall portion extending radially inward from the ceiling portion proximate the leading end, a second wall portion extending radially inward from the ceiling portion proximate the trailing end, a first floor portion extending from the first wall portion toward the second wall portion, and a second floor portion extending from the second wall portion toward the first wall portion, the ceiling portion defining a pocket beveled surface extending circumferentially inwardly from the first circumferential side, and the second circumferential side defining a platform sealing surface; anda damper having a leading end, a trailing end, a first circumferential side, a second circumferential side, a body portion, a radially-outward side, a first leg portion extending radially inwardly from the leading end of the body portion, a second leg portion extending radially inwardly from the trailing end of the body portion, the first circumferential side defining a damper sealing surface, the radially-outward side defining a damper beveled surface;the damper beveled surface slidingly engaged with the pocket beveled surface of a first of the plurality of platforms, and the damper movable with respect to the first of the plurality of platforms between a first position wherein at least a portion of the damper is recessed within the pocket of the first of the plurality of platforms and a second position wherein a lesser portion of the damper is recessed within the pocket of the first of the plurality of platforms and the damper sealing surface is engaged with a platform sealing surface of a second of the plurality of platforms adjacent the first of the plurality of platforms, wherein the first and second leg portions of the damper define respectively a first outer surface and a second outer surface, wherein the first outer surface and the second outer surface are in sliding engagement the first and second wall portions of the pocket, wherein the first and second leg portions of the damper define respectively a first foot and a second foot, wherein the first foot and the second foot are respectively engaged with the first and second floor portions when the damper is in the first position, and each platform further comprising a first lip extending radially outwardly from the first floor portion proximate a free end of the first foot and a second lip extending radially outwardly from the second floor portion proximate a free end of the second foot. 9. The turbine blade damping system of claim 8, further comprising a root extending radially inwardly from the radially-inward side of the platform. 10. The turbine blade damping system of claim 9, further comprising an airfoil extending radially outwardly from the radially-outward side of each of the plurality of platforms. 11. The turbine blade damping system of claim 8, each of the plurality of platforms attached to a wheel. 12. The turbine blade damping system of claim 8, wherein the body portion and the first leg of the damper cooperate to define the damper sealing surface. 13. The turbine blade damping system of claim 8, wherein the body portion, the first leg, and the second leg of the damper cooperate to define the damper sealing surface. 14. The turbine blade damping system of claim 8, further comprising a second damper having a leading end, a trailing end, a first circumferential side, a second circumferential side, a body portion, a radially-outward side, a first leg portion extending radially inwardly from the leading end of the body portion, a second leg portion extending radially inwardly from the trailing end of the body portion, the first circumferential side defining a damper sealing surface, the radially-outward side defining a damper beveled surface; the damper beveled surface slidingly engaged with the pocket beveled surface of the second of the plurality of platforms, and the damper movable with respect to the second of the plurality of platforms between a first position wherein at least a portion of the damper is recessed within the pocket of the second of the plurality of platforms and a second position wherein a lesser portion of the damper is recessed with the pocket of the second of the plurality of platforms and the damper sealing surface is engaged with a platform sealing surface of a third of the plurality of platforms adjacent the second of the plurality of platforms.

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Recessable damper for turbine

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특허 상세정보

Recessable damper for turbine

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이 특허에 인용된 특허 (19)

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