Turbofan with dynamic vibration damping
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0742010
(1991-08-08)
|
우선권정보 |
FR-0010107 (1990-08-08) |
발명자
/ 주소 |
- Vermont Grard R. E. R. (Coubert FRX)
|
출원인 / 주소 |
- Societe Nationale d\Etude et de Construction de Moteurs d\Aviation“S.N.E.M.C.A.” (Paris FRX 03)
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인용정보 |
피인용 횟수 :
10 인용 특허 :
0 |
초록
▼
A fan for a turboshaft engine is disclosed comprising a rotatable disc having an array of blades secured at evenly spaced intervals around its periphery, each pair of successive blades and the disc defining a space which is delimited by the stem and a platform of a first of the two blades, the stem
A fan for a turboshaft engine is disclosed comprising a rotatable disc having an array of blades secured at evenly spaced intervals around its periphery, each pair of successive blades and the disc defining a space which is delimited by the stem and a platform of a first of the two blades, the stem and a platform of the second of the two blades, and the periphery of the disc between the two blades. In order to reduce vibration during operation of the fan, each of the spaces houses a flyweight and a pair of rigid rockers disposed between the flyweight and the stems and platforms of the first and second blades delimiting the space such that, under the action of centrifugal force generated by rotation of the disc, the flyweight acts on the first and second blades through the rockers, the two rockers mutually engaging each other while a first of the rockers bears on the stem and the platform of the first blade at separate positions, the second of the two rockers bears on the stem and the platform of the second blade at separate positions, and the flyweight bears on both the first and the second rockers.
대표청구항
▼
A fan for a turboshaft engine comprising: a disc having an axis of rotation and a periphery defining a plurality of teeth spaced evenly apart around said disc and a plurality of recesses of dovetail-shaped cross-section disposed between said teeth, a plurality of blades secured to the periphery of s
A fan for a turboshaft engine comprising: a disc having an axis of rotation and a periphery defining a plurality of teeth spaced evenly apart around said disc and a plurality of recesses of dovetail-shaped cross-section disposed between said teeth, a plurality of blades secured to the periphery of said disc, each of said blades comprising a root having a dovetail shape corresponding to that of said recesses, said root being received in a respective one of said recesses, a stem extending radially outwards from said root, a profiled portion defining the blade proper disposed radially outwards from said stem, and two platforms extending transversely from said stem, one on each side thereof, at the junction between said stem and said profiled portion of the blade, said disc and said blades defining a plurality of spaces, each of said spaces being delimited by the stem and one of said platforms of a first of said blades, the stem and one of said platforms of a second of said blades adjacent said first blade, and the peripheral surface of said tooth disposed between the roots of said first and second blades, a plurality of flyweights disposed one in each of said spaces, and a plurality of rigid rockers disposed two in each of said spaces so that said two rockers are interposed between said flyweight in said space and the stems and platforms of said first and second blades delimiting said space such that, under the action of centrifugal force generated by rotation of said disc, said flyweight acts on said first and second blades through said rockers, said two rockers mutually engaging each other while a first of said rockers bears on the stem and the platform of said first blade at separate positions, the second of said two rockers bears on the stem and the platform of said second blade at separate positions, and said flyweight bears on both said first and said second rockers.
이 특허를 인용한 특허 (10)
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Chin Kevin, Aerofoil blade damper.
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Kayser, Andreas, Blade arrangement.
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Herbert Brandl DE; Rudolf Kellerer DE; Brammajyosula Ravindra CH, Blade arrangement with damping elements.
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Hogberg, Nicholas Alvin, Compressive stress system for a gas turbine engine.
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Tibbott, Ian; Dane, Edwin, Cooling arrangement.
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Schoenhoff, Carsten; Dopfer, Manfred; Pernleitner, Martin; Schuette, Wilfried, Damping means for damping a blade movement of a turbomachine.
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Bulgrin Charles A. ; Struthers John O., Offset center of gravity radial damper.
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Marchi Marc R. (Le Mee FRX) Taillant Jean-Claude C. (Vaux le Penil FRX), Seal for gas turbine rotor blades.
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Stiehler, Frank; Hein, Manuel, Sealing device, integrally bladed rotor basic body, and turbomachine.
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Lieser, Dirk; Reichert, Arnd; Strassberger, Micheal; Tiemann, Peter, Turbo-machine comprising a sealing system for a rotor.
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