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1. 发明授权

EP2953853B1 AVION SPATIAL 失效转让
标题翻译： RAUMFLUGZEUG
公开(公告)号：EP2953853B1
公开(公告)日：2016-11-23
申请号：EP14703108.2
申请日：2014-01-17
申请人： Airbus Defence and Space SAS
发明人： FERREIRA, Eugénio , PRAMPOLINI, Marco , CORABOEUF, Yohann
IPC分类号： F02C7/05 , F02C7/042 , B64G1/40 , B64G1/14 , B64D33/02
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/026 , B64G1/14 , B64G1/40 , F02C7/042 , F02C7/05

2. 发明授权

EP2871131B1 Variable geometry helicopter engine inlet 有权
公开(公告)号：EP2871131B1
公开(公告)日：2018-12-05
申请号：EP14191067.9
申请日：2014-10-30
申请人： Sikorsky Aircraft Corporation
发明人： Lamb Jr., Donald William
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0253 , F02C7/042 , Y10T137/0536
摘要： A variable area engine inlet (15) of a helicopter (10) is provided and includes first inlet portions (20) disposed to face one another in opposite directions and at a distance from one another and second inlet portions (21) extending between the first inlet portions (20) and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions (20, 21) define a capture area (150) and at least one or both of the first and second inlet portions (20, 21) include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area (150) and the second position is associated with a constricted condition of the capture area (150).

3. 发明授权

EP2678226B1 SELF-ALIGNING INLET PLENUM SYSTEM FOR ROTORCRAFT 有权
标题翻译：自对准入口压SYSTEM FOR A旋翼机
公开(公告)号：EP2678226B1
公开(公告)日：2015-01-21
申请号：EP11864163.8
申请日：2011-04-28
申请人： Bell Helicopter Textron Inc.
发明人： DAILEY, Zachary, E. , MAST, Thomas, M.
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/0293

4. 发明公开

EP3281876A1 INLET DUCT SELECTOR FOR TILTROTOR BARRIER FILTER 有权
标题翻译： TILTROTOR BARRIER FILTER的入口管道选择器
公开(公告)号：EP3281876A1
公开(公告)日：2018-02-14
申请号：EP17180144.2
申请日：2017-07-06
申请人： Bell Helicopter Textron Inc.
发明人： MILLER, David L. , ROSS, Brent Chadwick
IPC分类号： B64D33/02
CPC分类号： B64C7/02 , B64C27/14 , B64C29/0033 , B64D33/02 , B64D2033/0253 , B64D2033/0293
摘要： The present invention includes an air flow bypass for a tiltrotor engine (308) comprising: a ram air inlet (304) comprising bypass door(s) (306) capable of at least partially or fully blocking a ram air flow through the ram air inlet (304); a barrier filter inlet (302) positioned in a side, a bottom, and/or a top of a tiltrotor engine nacelle (208b, Figure 3A); a filter plenum (310); a selector duct (312) comprising one or more openings; and one or more selector duct doors or covers (322, Figure 6A) over the one or more openings; wherein the barrier filter inlet (302), the filter plenum (310), the one or more openings in the selector duct (312), the selector duct (312), and an engine (308) are in fluid communication and the bypass door(s) (306) in the ram inlet (304) are closed and the barrier filter inlet (302) provides filtered air flow to the engine (308) when the aircraft (100, Figure 1) is in hover operations.
摘要翻译：本发明包括用于倾转旋翼发动机（308）的气流旁路，其包括：包括旁路门（306）的冲压空气入口（304），所述旁路门能够至少部分地或完全地阻挡通过冲压空气入口（304）; 位于倾转旋翼发动机机舱（208b，图3A）的侧面，底部和/或顶部的屏障过滤器入口（302）; 过滤器增压室（310）; 选择器管道（312），其包括一个或多个开口; 和在一个或多个开口上方的一个或多个选择器管道门或盖（322，图6A）其中屏障过滤器入口（302），过滤器增压室（310），选择器管道（312）中的一个或多个开口，选择器管道（312）以及发动机（308）流体连通并且旁路门当飞行器（100，图1）处于悬停操作时，冲头入口（304）中的一个或多个（306）关闭且阻挡过滤器入口（302）向发动机（308）提供经过滤的空气流。

5. 发明授权

EP2853493B1 Helicopter with engine air intakes 有权
标题翻译：直升机发动机的进气设备
公开(公告)号：EP2853493B1
公开(公告)日：2016-08-10
申请号：EP13400021.5
申请日：2013-09-30
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Bräutigam, Ralf
IPC分类号： B64D33/02 , B64C27/04
CPC分类号： B64D33/02 , B64C27/04 , B64D27/02 , B64D2033/0253

6. 发明公开

EP2953853A1 AVION SPATIAL 失效转让
标题翻译：空天飞机
公开(公告)号：EP2953853A1
公开(公告)日：2015-12-16
申请号：EP14703108.2
申请日：2014-01-17
申请人： Astrium SAS
发明人： FERREIRA, Eugénio , PRAMPOLINI, Marco , CORABOEUF, Yohann
IPC分类号： B64D33/02 , B64C30/00 , B64G1/00 , B64G1/14 , B64G1/40 , F02K7/18
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/026 , B64G1/14 , B64G1/40 , F02C7/042 , F02C7/05
摘要： - According to the invention, said space aircraft comprises, at the front of each of the air inlets (5) of the turbo engines (4), a mobile flap (6) that can move, in both directions, between a first position for which said flap opens said air inlet (5) and a second position for which said flap prevents air from entering said air inlet (5).

7. 发明公开

EP2871131A1 Variable geometry helicopter engine inlet 有权
标题翻译： Hubschraubermotoreinlass mit variabler Geometrie
公开(公告)号：EP2871131A1
公开(公告)日：2015-05-13
申请号：EP14191067.9
申请日：2014-10-30
申请人： Sikorsky Aircraft Corporation
发明人： Lamb Jr., Donald William
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0253 , F02C7/042 , Y10T137/0536
摘要： A variable area engine inlet (15) of a helicopter (10) is provided and includes first inlet portions (20) disposed to face one another in opposite directions and at a distance from one another and second inlet portions (21) extending between the first inlet portions (20) and being disposed to face one another in opposite directions and at a distance from one another. The first and second inlet portions (20, 21) define a capture area (150) and at least one or both of the first and second inlet portions (20, 21) include a movable portion disposed to occupy and move between first and second positions. The first position is associated with a non-constricted condition of the capture area (150) and the second position is associated with a constricted condition of the capture area (150).
摘要翻译：提供直升机（10）的可变区域的发动机入口（15），并且包括第一入口部分（20），该第一入口部分（20）设置成彼此相反并且彼此间隔一定距离;以及第二入口部分入口部分（20）并且被设置为在相反的方向上彼此相对地彼此相对地彼此面对。第一入口部分（20）和第二入口部分（21）限定捕获区域（150），并且第一和第二入口部分（20,21）中的至少一个或两个包括设置成占据第一和第二位置。第一位置与捕获区域（150）的非限制状态相关联，并且第二位置与捕获区域（150）的收缩状态相关联。

8. 发明公开

EP2678226A1 SELF-ALIGNING INLET PLENUM SYSTEM FOR ROTORCRAFT 有权
标题翻译：自对准入口压SYSTEM FOR A旋翼机
公开(公告)号：EP2678226A1
公开(公告)日：2014-01-01
申请号：EP11864163.8
申请日：2011-04-28
申请人： Bell Helicopter Textron Inc.
发明人： DAILEY, Zachary, E. , MAST, Thomas, M.
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/0293
摘要： An inlet system for a rotorcraft includes a cowl door assembly and a plenum assembly. The cowl door assembly includes a door member, a cowl inlet opening, and a cowl inlet duct. The plenum assembly is configured to free float in relation to the cowl door. The plenum assembly includes a plenum duct with a plenum band configured to attach the plenum assembly to an inlet opening. An aft seal is located between the aft plenum flange and a firewall, the aft seal being configured to provide a compressive contact between the plenum assembly and the firewall.

9. 发明公开

EP3131817A4 ENGINE INLET CONFIGURATION 有权
公开(公告)号：EP3131817A4
公开(公告)日：2018-01-03
申请号：EP15779782
申请日：2015-04-13
申请人： SIKORSKY AIRCRAFT CORP
发明人： BOFILL STEVEN , CHASEN SCOTT A , SIMONETTI JOSEPH LAWRENCE , LAMB DONALD WILLIAM JR
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0246 , B64D2033/0253
摘要： An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.

10. 发明公开

EP2995556A1 An aircraft with an air intake for an air breathing propulsion engine 有权
标题翻译： Flugzeug mit Lufteinlassfürein Strahltriebwerk
公开(公告)号：EP2995556A1
公开(公告)日：2016-03-16
申请号：EP14400046.0
申请日：2014-09-12
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , Löser, Frank , Probst, Stefan , Matt, Michael
IPC分类号： B64D33/02 , F02C7/05
CPC分类号： B64D33/02 , B64C27/04 , B64D2033/022 , B64D2033/0253 , F02C7/052 , F02C7/055 , F05D2220/329 , F05D2260/607 , Y02T50/675
摘要： The invention is related to an aircraft 1 with a fuselage 2 that accommodates at least one air breathing propulsion engine 8a, said fuselage 2 having a maximum fuselage width determined in the region of said at least one air breathing propulsion engine 8a and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering said at least one air breathing propulsion engine 8a at least partly, said at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of said at least one air breathing propulsion engine 8a by a predetermined cowling offset to define a dynamic air intake 9 through which an intake air stream is supplied to said at least one air breathing propulsion engine 8a in operation.
摘要翻译：本发明涉及具有机身2的飞行器1，其具有容纳至少一个空气呼吸推进发动机8a的机身，所述机身2具有在所述至少一个空气呼吸推进发动机8a的区域中确定的最大机身宽度，并且包括至少一个前机身整流罩和至少一个后机身整流罩，其至少部分地覆盖所述至少一个空气呼吸推进发动机8a，所述至少一个前机身和后机身整流罩在横向于纵向轴线的方向上彼此间隔开的所述至少一个空气呼吸推进发动机8a通过预定的整流罩偏移来限定动态空气进口9，通过所述动态空气进气口9将所述至少一个空气呼吸推进发动机8a供应到运行中。

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