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71. 发明专利

FR2946696A1 DISPOSITIF D'INVERSION DE POUSSEE 未知
公开(公告)号：FR2946696A1
公开(公告)日：2010-12-17
申请号：FR0902807
申请日：2009-06-10
申请人： AIRCELLE SA
发明人： VAUCHEL GUY
IPC分类号： F02K1/64
摘要： L'invention concerne un dispositif d'inversion de poussée (20) comprenant au moins un capot mobile (30) monté en translation selon une direction sensiblement parallèle à un axe longitudinal d'une nacelle apte à passer alternativement d'une position de fermeture dans laquelle il assure la continuité aérodynamique de la nacelle à une position d'ouverture dans laquelle il ouvre un passage dans la nacelle destiné à un flux dévié, ledit capot mobile (30) étant également prolongé par au moins une section de tuyère variable (40) comprenant au moins un panneau (41) monté mobile en rotation, ledit panneau (41) étant adapté pour, d'une part, pivoter au moins vers une position entrainant une variation de la section de la tuyère (40) et, d'autre part, pivoter vers une position dans laquelle il obstrue une veine (13) de flux froid formée entre une structure fixe de carénage d'un turboréacteur (12) et la nacelle, le capot mobile (30) et le panneau (41) étant associés à des moyens d'actionnement (50) aptes à activer leur déplacement respectif en translation et en rotation caractérisé en ce que lesdits moyens d'actionnement (50) sont reliés à une extrémité amont du panneau (41) par une bielle d'entrainement (61) montée mobile autour de points d'ancrage respectivement sur le panneau (41) correspondant et sur les moyens d'actionnement (50) associés.

72. 发明专利

FR2855497B1 未知
公开(公告)号：FR2855497B1
公开(公告)日：2007-05-11
申请号：FR0400494
申请日：2004-01-20
申请人： ROLLS ROYCE PLC
发明人： JONES EMLYN , STRETTON RICHARD GEOFFREY
IPC分类号： B64D29/00 , B64D29/08 , F01D5/00 , F01D25/00 , F02C7/00 , F02C7/04 , F02C7/32 , F02K1/64
摘要： A nacelle ( 55 ) for a gas turbine engine ( 10 ), the engine ( 10 ) comprising accessories ( 34 ) mounted to a fan casing ( 28 ) and a core engine ( 9 ), the nacelle ( 55 ) substantially surrounds the engine ( 10 ) and comprises an intake ( 12 ) and a thrust reverser unit ( 31 ). The thrust reverser unit ( 31 ) is formed by two generally C-shaped portions ( 31 a, 31 b). The thrust reverser unit ( 31 ) is openable to provide access to the accessories ( 34 ) and the core engine ( 9 ). The nacelle ( 55 ) further comprises a fan containment casing ( 33 ) that is integral with the intake ( 12 ).

73. 发明专利

BRPI0414047A 未知
公开(公告)号：BRPI0414047A
公开(公告)日：2006-10-24
申请号：BRPI0414047
申请日：2004-08-31
申请人： NORDAM GROUP INC
发明人： LAIR JEAN-PIERRE
IPC分类号： E05B47/06 , E05B53/00 , E05C3/06 , F02K1/64 , F02K1/76
摘要： A thrust reverser includes reverser doors pivotally mounted in a nacelle. Each door includes a latch pin mounted at a distal end thereof. A complementary latch hook is pivotally mounted in the nacelle for engagement with the pin to latch closed the reverser door. A rotary retainer adjoins the hook for blocking rotation of the hook to latch closed the door, and selectively unblock rotation of the hook to permit the pin to disengage the hook.

74. 发明专利

GB2403774B Aeroengine nacelle 未知
公开(公告)号：GB2403774B
公开(公告)日：2006-09-06
申请号：GB0315800
申请日：2003-07-07
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY , JONES EMLYN
IPC分类号： B64D29/00 , B64D29/08 , F02C7/00 , F02C7/32 , F02K1/64

75. 发明专利

SU410669A1 СПОСОБ РЕГУЛИРОВАНИЯ ДВУХКОНТУРНОГО ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ 未知
公开(公告)号：SU410669A1
公开(公告)日：2005-06-27
申请号：SU1744238
申请日：1972-02-08
IPC分类号： F02K1/64
摘要： Способрегулированиядвухконтурноготурбореактивногодвигателяпутемподдержаниязаданнойстепениповышениядавлениявоздухав вентилятореизменениемплощадисеченияреактивногосопла, отличающийсятем, что, сцельюобеспеченияоптимальныххарактеристикдвигателя, измеряютстепеньповышениядавлениявоздухав компрессореи задаютстепеньповышениядавленияв вентиляторекакфункциюотстепениповышениядавленияв компрессоре.

76. 发明专利

GB2353983B Variable mode jet engine-suitable for STOVL 未知
公开(公告)号：GB2353983B
公开(公告)日：2003-10-15
申请号：GB0016310
申请日：2000-07-04
申请人： HUBBARD ADRIAN ALEXANDER
发明人： HUBBARD ADRIAN ALEXANDER
IPC分类号： B64C29/00 , F02K1/56 , F02K1/64 , F02K3/075 , F02K1/00 , B64C15/02
摘要： This jet engine comprises a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, ahead of which sits a larger diameter main fan unit 3 driven from the front of the secondary fan via a long drive shaft 4. A center portion of the main fan feeds the secondary fan via long central duct 5. The outer portion of the main fan is ducted into a split exhaust plenum chamber 6. This chamber has thrust vectoring exhaust mechanisms 7 immediately attached to each side, and then each side then feeds a thrust splitter 10, and then feeds to variable area outer ducting 8, using double-hinged inner and outer doors 9. Both outer ducts rejoin the central duct downstream in a second plenum chamber 11 just ahead of the secondary fan. Between this chamber and secondary fan is an intercooler 12.

77. 发明专利

FR2830051A1 Lock for aircraft gas turbine thrust reverser has bolts to selectively prevent movement of reverser guide rails 未知
公开(公告)号：FR2830051A1
公开(公告)日：2003-03-28
申请号：FR0112405
申请日：2001-09-27
申请人： HUREL HISPANO LE HAVRE
发明人： DEHU MICHEL PHILIPPE , LORE XAVIER RAYMOND YVES
IPC分类号： F02K1/72 , F02K1/76 , F02K1/64
摘要： The lock is for a bypass aircraft gas turbine thrust reverser with guides (60) for the movable reverser sections (50) having rails (64) attached to the movable sections (50) and slides (62) attached to longitudinal beams (36). The lock has locking assemblies (82) mounted at the end of each slideway in the opening direction. Each lock has a bolt (10) to selectively stop displacement of the rail in the opening direction.

78. 发明专利

FR2757215A1 未知
公开(公告)号：FR2757215A1
公开(公告)日：1998-06-19
申请号：FR9615256
申请日：1996-12-12
申请人： HISPANO SUIZA SA
发明人： GONIDEC PATRICK , ROUYER PASCAL GERARD , VAUCHEL GUY BERNARD
IPC分类号： B64D33/00 , F02K1/64 , F02K1/70
摘要： The thrust reversal system consists of a number of hinged doors (7) which form part of the outer wall of the by-pass flow duct behind the engine fan when closed, and are opened to deflect the flow outwards and forwards. The opening through which the flow is deflected is bounded at the forward end by a deflector edge attached to the engines fixed structure, and behind which is a deflector vane (8) which is designed to improve the orientation of the thrust reversal flow. The vane, which has an aerofoil section, is situated in the cavity beneath the forward end of the thrust reversal door when closed. In a variant of the design the system can have a series of deflector vanes which deploy as the door is opened.

79. 发明专利

FR2696212A1 Thrust reverser for gas turbine in aircraft - Has gates constructed of outer and inner skins with stiffeners and thermal insulation between 未知
公开(公告)号：FR2696212A1
公开(公告)日：1994-04-01
申请号：FR9211518
申请日：1992-09-28
申请人： AVIONS HUREL DUBOIS CONSTRUCTI
发明人： ALAIN FOURNIER
IPC分类号： F02K1/64 , F02K1/82 , F02K1/74
摘要： The power inverter, on a dual flow jet engine, has an exterior nozzle (1) at the end of the outlet duct (C). The flow of hot gas (Gc) from the nozzle (2) is surrounded by a flow of cool gas (Gf), which comes from an upstream fan. The assembly carries two gates (5), which are mounted pivotally, to lie to form a line with the outlet, or in the inverted position, to close off the outlet and divert the flow. The inner (11) skin of the gates and the parts (4) of the outlet are made of materials capable of supporting high temperatures. The external skin (10) of the gates and the internal stiffeners (12) are made of a light material less resistant to high temperature. USE/ADVANTAGE - It produces effective thrust reversal and long life from a simple low cost construction.

80. 发明专利

DE3683721D1 未知
公开(公告)号：DE3683721D1
公开(公告)日：1992-03-12
申请号：DE3683721
申请日：1986-05-13
申请人： BOEING CO
发明人： VERMILYE MICHAEL L
IPC分类号： B29C45/00 , B29C45/14 , B29C70/72 , B29D28/00 , B64C25/42 , B64D33/04 , F02K1/60 , F02K1/64 , F02K1/72 , F02K1/54

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