[특허]Mounting arrangement for a gas turbine engine

[미국특허] Mounting arrangement for a gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-027/00
출원번호	US-0244252 (1994-05-20)
우선권정보	GB-0025011 (1991-11-25)
국제출원번호	PCT/GB92/01576 (1992-08-28)
§371/§102 date	1994May2 (1994May2)
국제공개번호	WO-9311041 (1993-06-10)
발명자 / 주소	Taylor Mike C. (Derby GB2) Hodgkinson Carl (Derby GB2) Wright Kenneth W. (Derby GB2) Perry Derek (Derby GB2)
출원인 / 주소	Rolls-Royce plc (London GB2 03)
인용정보	피인용 횟수 : 44 인용 특허 : 0

초록 ▼

A gas turbine engine 10 is suspended via a casing 15 from a pylon 12 by a front mount 20 and a rear mount 40. The front mount 20 comprises a bracket 22, having a plurality of pins 26,28 and 30 integral therewith, which is bolted to the underside 11 of the pylon 12. The first pin 26 engages an annular flange 16 around the casing 15 to support the engine 10 in a vertical plane. Any vertical loads act peripherally of the casing 15 through the annular flange 16 to minimise the distortion of the casing 15. The second pin 28 engages with the casing 15 directly to prevent axial and lateral movement of the engine 10 relative to the pylon 12. The third pin 30 is provided as a failsafe. In normal operation the third pin 30 carries no load, however if the first pin 26 should break the third pin 30 then supports the engine 10 in a vertical plane. Any vertical loads then act peripherally of the engine casing 15 through an annular flange 18.

대표청구항 ▼

A mounting arrangement for a gas turbine engine (10) having a casing (15) provided with an at least one annular flange (16) comprising a support member (22) for attachment to an aircraft structure (12) from which the engine (10) is to be mounted, the support member (22) having a first connection means (26) which engages the at least one annular flange (16) on the engine casing (15) to support the engine (10) in a vertical plane, the vertical loads acting peripherally of the engine casing (15) through the annular flange (16), a second connection means: (28) which engages the engine casing (15) directly to prevent axial movement of the engine (10) relative to the aircraft structure (12) and a third connection means (30) which in normal operation carries no load unless the first connection means (26) breaks whereby the third connection means (30) engages with a further annular flange (18) on the engine casing (15) to support the engine (10) in a vertical plane, the vertical loads acting peripherally of the engine (15) casing through the further annular flange (18) characterised in that the first (26), second (28) and third (30) connection means are an integral part of the support member (22) and the support member (22) and connection means (26,28 and 30) are split in a direction parallel to the longitudinal axis of the engine (10) to render them damage tolerant.

이 특허를 인용한 특허 (44) 인용/피인용 타임라인 분석

Udall, Kenneth F; Beardsley, Peter K, Aeroengine mounting.
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Levert, Stephane; Beaufort, Jacques, Aircraft engine mount structure comprising two thrust links with transverse fitting.
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Dunstan Kent W., Aircraft engine thrust mount.
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Hey Kenneth E., Aircraft engine thrust mount.
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Dron,Sebastien, Aircraft engine with means of suspension from the structure of an aircraft.
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Mulcaire, Thomas G, Assembly comprising a gas turbine engine and a supporting pylon.
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Foster, Joseph P., Assembly with blind installation capability.
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Ellis Joe E. ; Stuart Alan R., Double failsafe engine mount.
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Diochon, Lionel; Petrissans, Isabelle; Seguin, Guillaume, Engine assembly for aircraft.
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Beaufort, Jacques; Dumont, Jean-Francois, Engine attachment for an assembly system mounted between an attachment strut and an aircraft engine.
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Stretton, Richard Geoffrey; Udall, Kenneth Franklin, Engine mount.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B., Engine mount system for a turbofan gas turbine engine.
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Suciu, Gabriel L.; Marx, Jon A.; Merry, Brian D.; Nordeen, Craig A.; Dye, Christopher M., Engine mounting configuration for a turbofan gas turbine engine.
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Hey Kenneth E. (Seattle WA), Fail-safe engine mount system.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine compressor arrangement.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine compressor arrangement.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
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Seaquist John D. ; Culbertson Chris, Horizontally opposed trunnion forward engine mount system supported beneath a wing pylon.
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Demoulin, Lambert Olivier Marie; Pavillet, Julien; Seize, Guilhem, In-line removable heat shield for a turbomachine suspension yoke.
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Ellis Joe E. ; Stuart Alan R., Integrated failsafe engine mount.
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Suciu, Gabriel L.; Merry, Brian D.; Franklin, David W. J.; Dye, Christopher M., Mounting system for a gas turbine engine.
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Suciu, Gabriel L.; Merry, Brian D.; Franklin, David W. J.; Dye, Christopher M., Mounting system for a gas turbine engine.
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Suciu, Gabriel L.; Merry, Brian D.; Marx, Jon A.; Dye, Christopher M., Mounting system for a gas turbine engine.
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Jiang, Yiwei; Blewett, Michael R., One degree-of-constraint semi-fusible gearbox mounting link.
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Cloft, Thomas G., Pylon and engine mount configuration.
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Demouzon Fran.cedilla.is Michel,FRX ; Fer Rene Pierre,FRX ; Huet Patrick Jean Alibert,FRX ; Marnas Laurent Pierre Elysee Gaston,FRX, Redundant front suspension system for a turboshaft engine.
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Demouzon Francis Michel,FRX ; Fer Rene Pierre,FRX ; Alibert Huet Patrick Jean,FRX ; Marnas Laurent Pierre Elysee Gaston,FRX, Redundant front suspension system for a turboshaft engine.
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Demouzon Francis Michel,FRX ; Fer Rene Pierre,FRX ; Huet Patrick Jean Alibert,FRX ; Marnas Laurent Pierre Elysee Gaston,FRX, Redundant front suspension system for a turboshaft engine.
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Chamberlain,Mark, Redundant gas turbine engine mounting arrangement.
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Marche, Herve; Raison, Fabien, Sail wing aircraft which includes an engine mounted on a pylon.
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Vauchel, Guy Bernard; Hillereau, Nicolas; Collier, Jerome; Cribelier, Jean-Francois, Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit.
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Dunstan Kent W. ; Hey Kenneth E., Three link failsafe engine mount.
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Hey Kenneth E. (Seattle WA), Three link failsafe engine mount.
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Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph B.; Lord, Wesley K.; Schwarz, Frederick M., Turbine section of high bypass turbofan.
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Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph B.; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
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Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph B.; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
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Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph Brent; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
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MacFarlane, Ian Alexander, Turboprop engine with compressor turbine shroud.
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Macfarlane, Ian Alexander, Turboprop engine with compressor turbine shroud.
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Jiang, Yiwei; Blewett, Michael R., Two degree-of-constraint semi-fusible gearbox mounting link.
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Whiteford Gerald P. (Waterford PA) Herbst Paul T. (Erie PA), Vibration isolation system including a passive tuned vibration absorber.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Mounting arrangement for a gas turbine engine 원문보기