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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
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
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.
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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
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
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。
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公开(公告)号：EP2479414B1
公开(公告)日：2015-06-10
申请号：EP12002710.7
申请日：2008-08-07
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
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.
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公开(公告)号：EP1978231B1
公开(公告)日：2012-02-29
申请号：EP08251152.8
申请日：2008-03-28
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公开(公告)号：EP2578864A1
公开(公告)日：2013-04-10
申请号：EP12197068.5
申请日：2008-08-07
发明人： Frank, Joel Hudson , James, Norman John , Wang, Shunsen Richard , Bryant, Lynoel McKleny , 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
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 (254,256) located at a rear of the engine nacelle (18). 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 (260) at a leading edge of the ring assembly. The upstream exit (260) 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 (320) partially enclose actuator components (270) 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（18）后部的环组件（254,256）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（260）。 上游出口（260）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。 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（320）部分地包围用于减小阻力的致动器部件（270）。
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公开(公告)号：EP1978231A3
公开(公告)日：2010-08-04
申请号：EP08251152.8
申请日：2008-03-28
发明人： Jones, Tony , Harvey, John Herbert , Bacon, Peter William , Hubberstey, Mark , Wharton, Brett John , Davies, Neil Charles , Roberts, Stephen Michael , Wylie, Steven Andrew
摘要： An actuator arrangement comprises an actuator (12) having a rotatable drive input, a motor (20, 64), and a drive transmission arrangement (22) for transmitting rotary drive from the motor (20, 64) to the rotatable drive input of the actuator (12), wherein the transmission arrangement (22) includes a telescopic drive coupling (30).
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公开(公告)号：EP2578864B1
公开(公告)日：2014-09-24
申请号：EP12197068.5
申请日：2008-08-07
发明人： Frank, Joel Hudson , James, Norman John , Wang, Shunsen Richard , Bryant, Lynoel McKleny , 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
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.
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公开(公告)号：EP1978231A2
公开(公告)日：2008-10-08
申请号：EP08251152.8
申请日：2008-03-28
发明人： Jones, Tony , Harvey, John Herbert , Bacon, Peter William , Hubberstey, Mark , Wharton, Brett John , Davies, Neil Charles , Roberts, Stephen Michael , Wylie, Steven Andrew
摘要： An actuator arrangement comprises an actuator (12) having a rotatable drive input, a motor (20, 64), and a drive transmission arrangement (22) for transmitting rotary drive from the motor (20, 64) to the rotatable drive input of the actuator (12), wherein the transmission arrangement (22) includes a telescopic drive coupling (30).
摘要翻译： 致动器装置包括具有可旋转的驱动输入的致动器（12），马达（20,64）和驱动传动装置（22），用于将旋转驱动器从马达（20,64）传递到可转动的驱动输入 致动器（12），其中所述变速器装置（22）包括伸缩式驱动联轴器（30）。
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公开(公告)号：EP2399827A2
公开(公告)日：2011-12-28
申请号：EP11250598.7
申请日：2011-06-17
申请人： Rohr, Inc.
CPC分类号： B64D33/04 , B64D29/06 , F02K1/09 , F02K1/72 , F05D2250/41 , Y02T50/672
摘要： A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member (108) having a track channel (110). The slider assembly translatably engages the track assembly. The slider assembly includes a slider body (152) configured to be received within the track channel. The slider assembly further includes a slider arm member (154) pivotably coupled to the slider body with a hinge joint (300) disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.
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公开(公告)号：EP2388193A2
公开(公告)日：2011-11-23
申请号：EP11250493.1
申请日：2011-04-26
申请人： Rohr, Inc.
摘要： A guide system for translating components of an aircraft engine nacelle includes a track assembly (106) and a slider assembly (150). The track assembly includes a track guide member (108) and a track liner (112) engaged therewith. The track guide member includes a track channel (109) configured to receive the track liner. The track liner defines an interior surface and includes a projection portion (120) projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion (154) configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion (156) extending from the head portion and outwardly of the track assembly.
摘要翻译： 用于平移飞机发动机机舱的部件的引导系统包括轨道组件（106）和滑块组件（150）。 轨道组件包括轨道引导构件（108）和与其接合的轨道衬套（112）。 导轨构件包括构造成接收轨道衬套的轨道通道（109）。 轨道衬套限定内表面，并且包括突出部分（120），突出部分（120）从轨道通道向内突出以限定凸面。 滑块组件可平移地接合轨道组件并且包括具有头部部分（154）的滑动构件，该头部构造成被容纳在轨道通道内。 头部限定基本上对应于轨道衬套的凸形表面的凹形表面并且被配置为与其配合。 滑动构件还包括从头部部分延伸到轨道组件的外侧的延伸部分（156）。
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