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1. 发明公开

EP4015796A2 SYSTEMS AND METHODS FOR EXPANDING AN OPERATING SPEED RANGE OF A HIGH SPEED FLIGHT VEHICLE 审中-实审转让
公开(公告)号：EP4015796A2
公开(公告)日：2022-06-22
申请号：EP21208921.3
申请日：2021-11-18
申请人： The Boeing Company
发明人： DYER, Richard S. , ROODE, Matthew J. , BOWCUTT, Kevin G. , FRANKLIN, Timothy H. , SILKEY, Joseph S.
IPC分类号： F02C7/04 , F02C7/141 , F02C7/143 , F02K1/08 , F02K3/10 , F02K3/105 , F02K1/82
摘要： Systems and methods for expanding an operating speed range of a high speed flight vehicle (102) include providing a turbine engine (100) with an inlet air duct (112), and positioning a heat exchanger (140) in the inlet air duct (112) to cool at least a portion of duct air flow (118) associated with an engine core (122). Additionally or alternatively, a nozzle assembly (200) includes a cowl (210) fluidly communicating with the turbine engine (100) and having a cowl internal surface (216) defining a cowl orifice (218), and a plug (230) defines a primary thrust surface (232). The plug (230) is supported relative to the cowl (210) so that a portion of the primary thrust surface (232) is disposed within the cowl orifice (218) to define a throat (242) therebetween. An actuator (248) is coupled to at least one of the cowl (210) or the plug (230), and is configured to generate relative movement between the cowl (210) and the plug (230), thereby to modify the throat (242).

2. 发明授权

EP3483416B1 VARIABLE NOZZLE APPARATUS 有权转让
公开(公告)号：EP3483416B1
公开(公告)日：2021-05-19
申请号：EP18192597.5
申请日：2018-09-04
发明人： MURPHY, Michael Joseph
IPC分类号： F02K1/15 , F02K1/46 , F02K1/08

3. 发明公开

EP3597894A1 SUPERSONIC AIRCRAFT TURBOFAN 无效转让
公开(公告)号：EP3597894A1
公开(公告)日：2020-01-22
申请号：EP19182551.2
申请日：2019-06-26
申请人： Rolls-Royce plc
发明人： Whurr, John , Hickey, Conor
IPC分类号： F02K1/08 , F02K1/09 , F02K1/34 , F02K1/38 , F02K1/48 , F02K1/12 , F02K3/06
摘要： The present disclosure relates to a turbofan engine having: an engine core having a centre axis and comprising in flow series a compressor, a combustor and a turbine; and a bypass duct surrounding the engine core, the bypass duct having a bypass duct exit area (A COLD ) at its downstream end. The engine further comprises an exhaust nozzle assembly comprising: coaxially arranged inner mixer and outer exhaust nozzles, the exhaust nozzle being axially downstream of said mixer nozzle; a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area (A HOT ); and an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area (A 8 ). The bypass duct exit area (A COLD ) and core exit area (A HOT ) are axially aligned at a mixing plane to form a mixing plane area (A MIX ). The turbofan engine has a transonic thrust condition, a supersonic cruise condition and a take-off condition. In the supersonic cruise condition, the exhaust throat area (A 8 ) is increased relative to the exhaust throat area (A 8 ). In the take-off condition, the core exit area (A HOT ) is increased relative to the core exit area (A HOT ) in the transonic condition, and the bypass duct exit area (A COLD ) is decreased relative to the bypass duct exit area (A COLD ) in the transonic condition.

4. 发明公开

EP3412902A1 GAS TURBINE WITH MOVEABLE EXHAUST PLUG 审中-公开
公开(公告)号：EP3412902A1
公开(公告)日：2018-12-12
申请号：EP18177104.9
申请日：2018-06-11
申请人： United Technologies Corporation
发明人： BENT, Andre L. , ZYSMAN, Steven H. , SAWYERS-ABBOTT, Nigel David
IPC分类号： F02K1/08 , F02K1/16 , F02K1/72
CPC分类号： F02K1/70 , F02C3/04 , F02K1/08 , F02K1/16 , F02K1/72 , F02K3/06 , F05D2260/57 , F05D2270/62 , F05D2270/65
摘要： An exhaust section (78) of a gas turbine engine includes an exhaust plug (58), and an exhaust nozzle (60) radially offset from the exhaust plug defining an exhaust pathway (80) between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser (68) to divert a fan airflow (70) from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.

5. 发明公开

EP3366907A1 KONVERGENT-DIVERGENTE SCHUBDÜSE FÜR EIN TURBOFAN-TRIEBWERK EINES ÜBERSCHALLFLUGZEUGS UND VERFAHREN ZUR EINSTELLUNG DER DÜSENHALSFLÄCHE IN EINER SCHUBDÜSE EINES TURBOFAN-TRIEBWERKS 有权
公开(公告)号：EP3366907A1
公开(公告)日：2018-08-29
申请号：EP18158530.8
申请日：2018-02-26
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： TODOROVIC, Predrag
IPC分类号： F02K1/08 , F02K3/06
摘要： Die Erfindung betrifft eine konvergent-divergente Schubdüse (1) für ein Turbofan-Triebwerk eines Überschallflugzeugs, wobei die Schubdüse (1) eine Innenwand (11) aufweist und einen Strömungskanal (15) mit einer Düsenhalsfläche (A81, A82) und einer Düsenaustrittsfläche (A9) ausbildet. Es ist ein zwischen einer ersten Position und einer zweiten Position in axialer Richtung verschiebbarer Verkleidungsring (2) vorgesehen, wobei die Innenwand (11) der Schubdüse (1) und der Verkleidungsring (2) derart ausgebildet und zueinander positioniert sind, dass der Verkleidungsring (2) in der ersten Position radial beabstandet zur Innenwand (11) verläuft, wobei ein ringförmiger Bypass-Kanal (3) bereitgestellt ist, der zwischen dem Verkleidungsring (2) und der Innenwand (11) der Schubdüse (1) verläuft, wobei der Bypass-Kanal (3) eine zusätzliche Querschnittsfläche des Strömungskanals (15) bereitstellt, und der Verkleidungsring (2) in der zweiten Position an der Innenwand (81) anliegt.

6. 发明授权

EP2093407B1 Gas turbine engine with variable area fan nozzle bladder system and method of varying such fan nozzle exit area. 有权转让
标题翻译：具有可变面积风扇喷嘴气囊系统的燃气涡轮发动机以及改变这种风扇喷嘴出口面积的方法。
公开(公告)号：EP2093407B1
公开(公告)日：2018-04-04
申请号：EP09250406.7
申请日：2009-02-16
申请人： United Technologies Corporation
发明人： Stern, Alfred M.
IPC分类号： F02K1/08 , F02K1/00 , F02K1/15
CPC分类号： F02K1/085 , F02K1/002 , F02K1/10 , F02K1/15
摘要： A turbofan engine (10) includes a variable area fan nozzle (42) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio of the bypass flow with a multitude of bladders (52A...52D) circumferentially located about a core cowl (12). A method of varying such a fan nozzle exit area with a bladder system is also disclosed.

7. 发明授权

EP2420665B1 Variable area fan nozzle 有权转让
标题翻译：可变区风扇喷嘴
公开(公告)号：EP2420665B1
公开(公告)日：2015-10-28
申请号：EP11169267.9
申请日：2011-06-09
申请人： United Technologies Corporation
发明人： Murphy, Michael J.
IPC分类号： F02K1/06 , F02K1/08 , F02K1/15 , F02K3/06
CPC分类号： F02K1/06 , F02K1/08 , F02K1/15 , F02K3/06

8. 发明授权

EP2646673B1 THRUST REVERSER AND VARIABLE AREA FAN NOZZLE ACTUATION SYSTEM AND METHOD 失效
标题翻译：推力反向器以及系统和一种用于操作鼓风口面积可调
公开(公告)号：EP2646673B1
公开(公告)日：2015-07-22
申请号：EP11785204.6
申请日：2011-10-31
申请人： The Boeing Company
发明人： BURGESS, Michael John
IPC分类号： F02K1/06 , F02K1/08 , F02K1/16 , F02K1/54 , F02K1/64 , F02K1/09 , F02K1/76
CPC分类号： F02K1/763 , F02K1/06 , F02K1/08 , F02K1/09 , F02K1/16 , F02K1/54 , F02K1/64 , F02K1/76 , F15B15/088 , F15B15/261 , Y02T50/671 , Y02T50/677

9. 发明公开

EP2828490A1 TUYÈRE À SECTION VARIABLE ET NACELLE POUR TURBORÉACTEUR D'AÉRONEF ÉQUIPÉE D'UNE TELLE TUYÈRE 审中-公开
标题翻译：兰斯有变截面和飞机涡轮喷气发动机GONDOLA这样的枪
公开(公告)号：EP2828490A1
公开(公告)日：2015-01-28
申请号：EP13719903.0
申请日：2013-03-19
申请人： Aircelle
发明人： HURLIN, Hervé , MAALIOUNE, Hakim , KERBLER, Olivier
IPC分类号： F01D17/14 , F02K1/08 , F02K1/15
摘要： Variable-section jet pipe (3) for aircraft nacelle (1), of which at least one part (V1, V2, V3; B) is able to move between at least one position of smaller cross section and at least one position of larger cross section, and means for moving said part between said positions, these movement means firstly comprising piezoelectric actuators (P, Pa
1 , P2), and secondly comprising means of controlling these actuators.

10. 发明公开

EP2278146A3 Actuation system for a translating variable area fan nozzle 有权
标题翻译：驱动系统的扁平喷嘴，实现各领域的
公开(公告)号：EP2278146A3
公开(公告)日：2012-02-29
申请号：EP10005249.7
申请日：2010-05-19
申请人： Rohr, Inc.
发明人： Ramlaoui, Jihad I. , Amkraut, Daniel , Pinto, Geoffrey , Shetzer, Daniel , Hawksworth, Andrew Robert , Harvey, John , Evans, Alan K. , Chandarana, Vikram , Moorhouse, Roger
IPC分类号： F02K1/06 , F02K1/08 , F02K1/12 , F02K1/15 , F02K1/32 , F02K3/06
CPC分类号： F02K1/06 , F02K1/08 , F02K1/12 , F02K1/15 , F02K1/32 , F02K3/06
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

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