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1. 发明公开

EP3318494A1 FAN NACELLE TRAILING EDGE 有权转让
标题翻译：风扇NACELLE TRAILING EDGE
公开(公告)号：EP3318494A1
公开(公告)日：2018-05-09
申请号：EP17190324.8
申请日：2017-09-11
申请人： The Boeing Company
发明人： HOWE, Sean P.
IPC分类号： B64D33/04 , F02K1/00 , F02K1/12 , F02K1/30 , F02K1/70 , F02K1/15
CPC分类号： F02K1/18 , B64D27/18 , B64D31/06 , B64D33/04 , F01D25/24 , F02K1/00 , F02K1/12 , F02K1/15 , F02K1/30 , F02K1/70 , F02K1/82 , F04D27/001 , F04D29/522 , F04D29/545 , F05D2220/323 , F05D2250/324 , F05D2270/3015
摘要： A fan nacelle (104), a gas turbine engine cell assembly (190), and an aircraft are provided. The fan nacelle (104) includes a fan duct skin (110) arranged in a fan duct (112) to direct airflow from the fan of a Turbofan engine toward a fan nozzle (122). An exterior skin (114) of the fan nacelle directs air flow around an exterior of the engine. The fan duct skin (110) and the exterior skin (114) terminate at a trailing edge (108), and a trailing edge portion of the exterior skin is one of parallel to and diverging from a trailing edge portion of the fan duct skin in an aft direction. In certain aspects, the trailing edge portion of the exterior skin is actuatable or inflatable to selectively divert from the trailing edge portion of the fan duct skin.
摘要翻译：提供风扇机舱（104），燃气涡轮发动机单元组件（190）和飞机。风扇机舱（104）包括布置在风扇管道（112）中的风扇管道蒙皮（110），以将来自涡轮风扇发动机的风扇的气流引向风扇喷嘴（122）。风扇机舱的外部蒙皮（114）引导气流围绕发动机的外部。风扇管道蒙皮（110）和外部蒙皮（114）终止于后缘（108）处，并且外部蒙皮的后缘部分与风扇管道蒙皮的后缘部分平行并从其中分散出来尾部方向。在某些方面，外部蒙皮的后缘部分是可致动的或可膨胀的以选择性地从风扇管道蒙皮的后缘部分转向。

2. 发明授权

EP2665909B1 NACELLE POUR UN TURBORÉACTEUR D'AÉRONEF DOUBLE FLUX 失效转让
标题翻译： NACELLE POUR UNTURBORÉACTEURD'AÉRONEFDOUBLE FLUX
公开(公告)号：EP2665909B1
公开(公告)日：2017-09-13
申请号：EP12702596.3
申请日：2012-01-09
申请人： Safran Nacelles
发明人： GONIDEC, Patrick , BLIN, Laurent Albert
IPC分类号： F02K1/30 , B64C21/02 , B64D33/02 , B64D33/04 , F02C7/04 , B64D33/00 , F02C7/00 , F02K3/06
CPC分类号： B64D29/06 , B64D33/02 , B64D2033/0226 , B64D2033/0266 , B64D2033/0273 , B64D2033/0286 , F02C7/042 , F02C7/047 , F02K1/30 , Y02T50/671 , Y10T137/0536

3. 发明公开

EP2447519A3 Gas turbine engine with variable area fan nozzle 有权转让
标题翻译：燃气涡轮发动机风扇喷嘴具有可调节的
公开(公告)号：EP2447519A3
公开(公告)日：2014-12-10
申请号：EP11186846.9
申请日：2011-10-27
申请人： United Technologies Corporation
发明人： Hall, Andre M. , Kohlenberg, Gregory A. , Gilson, Jonathan
IPC分类号： F02K1/30 , F02K1/09 , B64D29/06 , B64D33/04
CPC分类号： F02K1/30 , B64D33/04 , F02K1/09 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A bypass gas turbine engine (10) includes a variable area fan nozzle (42) with a second fan nacelle section (54) axially movable relative to a first fan nacelle (52) section to define an auxiliary port to vary a fan nozzle exit area (44) and adjust fan bypass airflow. The second fan nacelle section (54) includes a leading edge region (54L) that defines a concave external contour and the first fan nacelle section (52) includes a trailing edge (52T) region that defines a convex internal contour.

4. 发明公开

EP2660442A3 Integrated thermal protection and leakage reduction in a supersonic air intake system 审中-公开
标题翻译：集成的热保护和减少渗漏的超音速进气系统
公开(公告)号：EP2660442A3
公开(公告)日：2014-09-24
申请号：EP13166256.1
申请日：2013-05-02
申请人： Lockheed Martin Corporation
发明人： Leland, Brad C. , Tworek, Andrew J. , Cho, Chan
IPC分类号： F02C7/057 , B64C21/06 , F02C9/18 , F02K1/30 , F02C7/141 , F02K7/10 , B64D33/02
CPC分类号： B64D33/02 , B64D2033/026 , F02C7/057 , F02C7/141 , F02C9/18 , F02K1/30 , F02K7/10 , F05D2220/80 , F05D2270/17 , Y02T50/671 , Y02T50/675 , Y10T137/0536
摘要： An air intake system suitable for a supersonic vehicle is disclosed. The system includes a channel comprising an inlet and a side wall and a plenum coupled to the side wall. The plenum is configured to accept a flow of coolant. In certain embodiments, the coolant is the waste coolant from an on-board electronics cooling system. The system also includes a porous region in the side wall configured to allow a flow of bleed air from the channel through the porous region of the side wall into the plenum so as to aid the transition to supersonic flow. In certain embodiments, the flow of the bleed air is reduced at supersonic speeds by pressurization of the plenum with the coolant.

5. 发明公开

EP2607676A2 Dual function cascade integrated variable area fan nozzle and thrust reverser 审中-公开
标题翻译： IntegrierteGebläsedüsemit variablem Querschnitt und Schubumkehrvorrichtung mit Doppelfunktionskaskade
公开(公告)号：EP2607676A2
公开(公告)日：2013-06-26
申请号：EP12195283.2
申请日：2012-12-03
申请人： United Technologies Corporation
发明人： Marshall, Richard M.
IPC分类号： F02K1/72 , F02K1/30 , F02K1/74
CPC分类号： F02K1/72 , F02K1/30 , F02K1/74 , Y02T50/671
摘要： A gas turbine engine (10) includes a core engine defined about an axis (A), a fan (14) driven by the core engine about the axis (A) to generate bypass flow (D), and at least one integrated mechanism (30) in communication with the bypass flow (D). The bypass flow (D) defines a bypass ratio greater than about six. The at least one integrated mechanism (30) includes a variable area fan nozzle (VAFN) (40) and thrust reverser (42), and a plurality of positions to control bypass flow (D).
摘要翻译：燃气涡轮发动机（10）包括围绕轴线（A）限定的核心发动机，由所述核心发动机围绕轴线（A）驱动以产生旁路流（D）的风扇（14），以及至少一个综合机构 30）与旁路流（D）通信。旁路流（D）限定大于约六的旁路比。至少一个集成机构（30）包括可变区域风扇喷嘴（VAFN）（40）和推力反向器（42）以及多个位置以控制旁路流（D）。

6. 发明公开

EP2479414A3 Variable area fan nozzle with bypass flow 有权
标题翻译：可调风扇喷嘴与旁路电流
公开(公告)号：EP2479414A3
公开(公告)日：2013-02-20
申请号：EP12002710.7
申请日：2008-08-07
申请人： Rohr, Inc. , Goodrich Actuation Systems Limited
发明人： Frank, Joel Hudson , James, Norman John , Wang, Shunsen Richard , Bryant, Lynoel McKleny , Baer, David , Jones, Tony , Harvey, John , Bacon, Peter , Hubberstey, Mark , Wharton, Brett , Davies, Neil , Roberts, Stephen Michael , Wylie, Steven Andrew
IPC分类号： F02K1/09 , F02K1/30 , F02K1/72 , F02K3/06
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.

7. 发明公开

EP2549105A1 Synthetic jet apparatus 有权
标题翻译： Synthetische JetFördervorrichtung
公开(公告)号：EP2549105A1
公开(公告)日：2013-01-23
申请号：EP12169697.5
申请日：2012-05-29
申请人： Lockheed Martin Corporation (Maryland Corp.)
发明人： Bennett, Grover , Boespflug, Matthew , Saddoughi, Seyed
IPC分类号： F04B17/00 , F04B43/04 , B64C21/00 , B64C23/06 , F02K1/28 , F02K1/30 , F15D1/08 , H01L27/20 , H01L41/09
CPC分类号： F04B17/003 , F02K1/28 , F02K1/30 , F04B43/046
摘要： A synthetic jet apparatus includes a series of generally parallel spaced-apart bimorph piezoelectric plates (12', 26, 40, 42) defining first and second sets of fluid chambers (14', 34) (16', 28). The chambers of the second set of fluid chambers (16', 28) are interleaved with the chambers of the first set of fluid chambers (14', 34). The first and second sets of fluid chambers are in fluid communication with sources of first and second fluids (18', 20'), respectively, the source (18') of the first fluid being separate from the source (20') of the second fluid. The bimorph plates are operable to alternately increase and decrease the volumes of the first and second set of fluid chambers by alternatively bowing towards and away from respective chambers in response to application of voltages of alternating polarity across the plates. The result of this is to alternate draw the first fluid from its source into the first set of fluid chambers while expelling the second fluid from the second set of fluid chambers, and then expel the first fluid from the first set of fluid chambers back into its source while drawing the second fluid from its source into the second set of fluid chambers.
摘要翻译：合成喷射装置包括限定第一和第二组流体室（14'，34）（16'，28）的一系列大致平行的间隔开的双压电晶片压电板（12'，26,40,42）。第二组流体室（16'，28）的腔室与第一组流体室（14'，34）的腔室交错。第一和第二组流体室分别与第一和第二流体（18'，20'）的源流体连通，第一流体的源极（18'）与源极（20'）分离，第二流体。双压电晶片板可操作以响应于在板上施加交替极性的电压而交替地增加和减小第一组和第二组流体室的体积，以便朝向和远离各个室弯曲。其结果是交替地将第一流体从其源引导到第一组流体室中，同时从第二组流体室排出第二流体，然后将第一流体从第一组流体室排出回到其中同时将第二流体从其源引入第二组流体室。

8. 发明公开

EP2479414A2 Variable area fan nozzle with bypass flow 有权
标题翻译： VerstellbareFandüsemit Bypass-Strom
公开(公告)号：EP2479414A2
公开(公告)日：2012-07-25
申请号：EP12002710.7
申请日：2008-08-07
申请人： Rohr, Inc. , Goodrich Actuation Systems Limited
发明人： Frank, Joel Hudson , James, Norman John , Wang, Shunsen Richard , Bryant, Lynoel McKleny , Baer, David , Jones, Tony , Harvey, John , Bacon, Peter , Hubberstey, Mark , Wharton, Brett , Davies, Neil , Roberts, Stephen Michael , Wylie, Steven Andrew
IPC分类号： F02K1/09 , F02K1/30 , F02K1/72 , F02K3/06
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.
摘要翻译：喷嘴组件的出口区域通过平移位于发动机机舱后部的环组件来改变。环可以沿着发动机的轴线轴向平移。当环转动时，环的后缘限定可变的喷嘴出口区域。环的翻译在环组件的前缘形成上游出口。上游出口可用于排放或以其他方式溢出来自发动机旁路管道的流量过剩。当发动机在各种飞行条件下运行时，可以平移环以获得较低的风扇压力比，从而提高发动机的效率。整流罩部分地包围致动器部件以减少阻力。

9. 发明授权

EP2181262B1 VARIABLE AREA FAN NOZZLE WITH BYPASS FLOW 有权
标题翻译： CHANGING风扇喷嘴具有旁路电力
公开(公告)号：EP2181262B1
公开(公告)日：2012-05-16
申请号：EP08828100.1
申请日：2008-08-07
申请人： Rohr, Inc. , Goodrich Actuation Systems Limited
发明人： FRANK, Joel Hudson , JAMES, Norman John , WANG, Shunshen Richard , MCKLENY, Bryant Lynoel , BAER, David A. , JONES, Tony , HARVEY, John H. , BACON, Peter W. , HUBBERSTEY, Mark , WHARTON, Brett J. , DAVIES, Neil C. , ROBERTS, Stephen Michael , WYLIE, Steven Andrew
IPC分类号： F02K1/09 , F02K1/30 , F02K1/72 , F02K3/06
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.

10. 发明授权

EP1918561B1 Combustion nozzle fluidic injection assembly 有权
标题翻译：液体注射组件用于燃烧喷嘴
公开(公告)号：EP1918561B1
公开(公告)日：2012-05-16
申请号：EP07254223.6
申请日：2007-10-24
申请人： United Technologies Corporation
发明人： Berg, Gerald R. , Lidstone, Gary L. , Messersmith, Nathan L. , Hinkey, John
IPC分类号： F02K1/30 , F02K1/28 , F02K1/38 , F02K7/02
CPC分类号： F02C6/08 , F02K1/002 , F02K1/28 , F02K1/38 , F02K7/02 , F02K9/82

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