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1. 发明申请

WO2018200941A1 AIRCRAFT FILTER SYSTEM WITH AIRSPEED COMPENSATION 审中-公开
公开(公告)号：WO2018200941A1
公开(公告)日：2018-11-01
申请号：PCT/US2018/029774
申请日：2018-04-27
申请人： DONALDSON COMPANY, INC.
发明人： BOYCE, Mark, E. , BROWN, Matthew, A.
IPC分类号： B64C27/04
CPC分类号： B64D33/02 , B01D46/0068 , B01D46/0086 , B01D2279/60 , B64C27/04 , B64D27/02 , B64D45/00 , B64D2033/0246 , B64D2045/0085 , F02C7/05 , F02C7/052 , G01N15/0826 , G01N2015/084
摘要： A system and method of compensating for airspeed when measuring pressure drop across a filter system on an aircraft may include a pressure compensator, an internal pressure sensor, and an external pressure sensor. A filter media may be located around a housing such that air flows through the filter media into a clean air space defined by the filter media and the housing. The pressure compensator may be located outside of the clean air space and within an airstream of the aircraft. The internal pressure sensor may be configured to measure an internal pressure that varies with airspeed and the external pressure sensor may be located on the pressure compensator to measure an external pressure. The external pressure sensor may be positioned such that the external pressure varies according to a known relationship relative to the internal pressure as the airspeed of the aircraft changes.

2. 发明申请

WO2013177263A1 ENGINE INLET 审中-公开
标题翻译：发动机进线
公开(公告)号：WO2013177263A1
公开(公告)日：2013-11-28
申请号：PCT/US2013/042195
申请日：2013-05-22
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： LAMB, Donald William Jr. , SIMONETTI, Joseph Lawrence
IPC分类号： F02C7/04 , B64D33/02
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0246 , F05D2260/606
摘要： An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urging an inlet airflow into two or more duct openings disposed at a fuselage of the aircraft. The inlet airflow is urged through two or more converging inlet duct legs extending from the two or more duct openings toward an engine inlet. A portion of the inlet airflow is flowed from at least one inlet duct leg of the two or more inlet duct legs into a pressure relief pathway. An inlet duct for an engine or multiple engines includes one or more inlet duct legs and a bypass leg extending from an inlet duct leg of the one or more inlet duct legs through a bypass opening.
摘要翻译：用于发动机或多个发动机的入口管道包括两个或更多个连接管道腿和位于每个管道腿部处以调节来自管道腿的入口气流的压力释放通路。一种操作飞行器的方法包括将入口气流推到布置在飞行器的机身上的两个或更多个管道开口中。入口气流通过从两个或更多个管道开口延伸到发动机入口的两个或更多个会聚的入口管道支柱被推动。入口气流的一部分从两个或更多个入口管道腿的至少一个入口管道腿流入压力释放通路。用于发动机或多个发动机的入口管道包括一个或多个入口管道腿和从一个或多个入口管道腿的入口管道腿通过旁路开口延伸的旁路腿。

3. 发明申请

WO2008130725A2 COMB FOR INLET BARRIER FILTER SYSTEM 审中-公开
标题翻译：用于入口过滤器系统
公开(公告)号：WO2008130725A2
公开(公告)日：2008-10-30
申请号：PCT/US2008051063
申请日：2008-01-15
申请人： AEROSPACE FILTRATION SYSTEMS I , BELYEW ROBERT R
发明人： BELYEW ROBERT R
IPC分类号： B01D46/52
CPC分类号： B01D46/523 , B01D46/0002 , B64D33/02 , B64D2033/0246 , F02C7/055 , F05D2220/329 , F05D2250/711 , Y02T50/671
摘要： An inlet barrier filter system for mounting on an aircraft to filter air prior to intake into an engine of the aircraft includes a frame having at least two curved frame members defining an opening. A filter element has a curved inward face and is received in the opening of the frame. The filter element includes filter media having pleats. A comb is attached to the frame and includes spaced-apart teeth that support the pleats. The comb is curved to generally conform to the curved inward face of the filter element.
摘要翻译：用于安装在飞机上以在进入飞行器的发动机之前过滤空气的入口阻挡滤清器系统包括具有限定开口的至少两个弯曲框架构件的框架。过滤元件具有弯曲的内表面并被接收在框架的开口中。过滤元件包括具有褶皱的过滤介质。梳子连接到框架上，并且包括支撑褶的间隔开的齿。梳子弯曲成大体上符合过滤元件的弯曲内表面。

4. 发明申请

WO2017089730A1 TURBOMACHINE COMPRENANT UN PIÈGE DE CORPS ÉTRANGERS CIRCULANT DANS UN FLUX D'AIR 审中-公开
标题翻译：使用冷阱身体的移动，对外AIR式水轮机
公开(公告)号：WO2017089730A1
公开(公告)日：2017-06-01
申请号：PCT/FR2016/053104
申请日：2016-11-25
申请人： SAFRAN AIRCRAFT ENGINES
发明人： FERRIER, Romain, Jean-Claude , BROGNA, Romeo , PROUTEAU, Jackie, Raymond, Julien , SIRVIN, Nicolas, Joseph
IPC分类号： F02C6/20 , F02C7/052 , F02C7/055 , B64D33/02
CPC分类号： F02C7/052 , B64D33/02 , B64D2033/022 , B64D2033/0246 , B64D2033/0293 , F02C6/206 , F02C7/055 , F05D2220/325 , F05D2260/607 , Y02T50/671 , Y02T50/675
摘要： L'invention concerne une turbomachine (24) de type «open rotor» ou turbopropulseur comprenant une nacelle (26) définissant une entrée (28) d'air, un moyeu (30) central et une veine (32) annulaire d'admission d'air entourant le moyeu (30) central et débouchant dans une veine (34) principale d'alimentation en air, le moyeu (30) central comprenant un piège (36) central ayant une ouverture (38) pour piéger les corps étrangers dans un flux d'air entrant dans la turbomachine (24),et une voie (48) de récupération d'air ayant un débouché (48a), par lequel ladite voie (48) de récupération d'air débouche dans la veine (34) principale, situé sur le moyeu (30) central.
摘要翻译：
本发明涉及一种涡轮发动机（24）类型＆LAQUO;空心转子＆RAQUO; 或涡轮螺旋桨发动机包括机舱（26）取消结束空气的项E E（28），轮毂（30）和中央静脉（32）的环形进气口周围的轮毂（30）的中心和DE ;插入到静脉（34），一次空气供应，所述轮毂（30）居中地包括PI＆egrave; GE（36）居中地在流中为PIéGER体（e）外国的开口（38）进入涡轮机（24）的空气以及具有封闭件的空气回收气道（48）部分（48a），其中所述通道（48）R E罩杯é配给空气Dé口进入静脉（34）主要位于Dé 在中心枢纽（30）上。

5. 发明申请

WO2013103416A3 FILTER SYSTEMS FOR AIR INTAKES OF AIRCRAFT ENGINES AND RELATED METHODS 审中-公开
标题翻译：用于飞机引擎的空气引入的过滤系统和相关方法
公开(公告)号：WO2013103416A3
公开(公告)日：2013-08-29
申请号：PCT/US2012059460
申请日：2012-10-10
申请人： AEROSPACE FILTRATION SYSTEMS INC
发明人： BOYCE MARK EDWARD
IPC分类号： B01D46/00 , B01D46/10 , B01D46/12 , B64D33/02 , F02C7/052
CPC分类号： F02C7/052 , B01D46/0087 , B01D46/103 , B01D46/12 , B01D2273/10 , B64C27/04 , B64D33/02 , B64D2033/0246 , F05D2220/329 , F16K31/06 , Y10T29/49233 , Y10T137/794
摘要： Aircrafts, methods, and filter systems for air intakes of aircraft engines are disclosed. One example filter system includes a filter assembly having an interior, a first end defining a bypass opening, and a second end for coupling to an air intake of an aircraft engine to permit intake air from the interior to enter the air intake. The filter assembly defines a substantially annular cross-section and includes at least one filter media for removing contaminants from intake air entering the interior through the filter media. The filter system includes a bypass closure movable relative to the filter assembly between at least a first position and a second position.
摘要翻译：公开了用于飞机发动机进气口的飞机，方法和过滤系统。一个示例过滤器系统包括具有内部，限定旁路开口的第一端和用于耦合到飞机发动机的进气口以允许来自内部的进气进入进气口的第二端的过滤器组件。过滤器组件限定大致环形的横截面并且包括至少一个过滤介质，用于从通过过滤介质进入内部的进气中去除污染物。过滤器系统包括可在至少第一位置和第二位置之间相对于过滤器组件移动的旁路闭合件。

6. 发明申请

WO2006113388A2 INTEGRATED ENGINE AIR PARTICLE FILTER ASSEMBLY 审中-公开
标题翻译：集成发动机空气颗粒过滤器总成
公开(公告)号：WO2006113388A2
公开(公告)日：2006-10-26
申请号：PCT/US2006/013976
申请日：2006-04-13
申请人： SIKORSKY AIRCRAFT CORPORATION , BARNARD, Richard, S. , PETERS, Jon, C.
发明人： BARNARD, Richard, S. , PETERS, Jon, C.
IPC分类号： B01D46/42
CPC分类号： B01D46/002 , B01D46/0013 , B01D46/008 , B01D46/10 , B01D2265/06 , B01D2279/60 , B64D33/02 , B64D2033/0246
摘要： An engine air particle filter system in a helicopter having a support structure that is fixed to the helicopter. The support structure has a plurality of ribs. The plurality of ribs and the support structure form a plurality of openings. A plurality of trays, containing a filter media, each fit into each one of the plurality of openings in an airtight configuration. A connector releasably secures each one of the plurality of trays to the support structure so that each one of the plurality of trays can be selectively inserted and withdrawn from each one of the plurality of openings.
摘要翻译：直升机中的发动机空气颗粒过滤系统具有固定在直升机上的支撑结构。支撑结构具有多个肋。多个肋和支撑结构形成多个开口。包含过滤介质的多个托盘分别以气密构造装配到多个开口中的每一个中。连接器可释放地将多个托盘中的每个托盘固定到支撑结构，使得多个托盘中的每一个托盘可以选择性地从多个开口中的每个开口插入和拉出。

7. 发明申请

WO2014200590A2 INTERCHANGEABLE INLET PROTECTION SYSTEMS FOR AIR INTAKES OF AIRCRAFT ENGINES AND RELATED METHODS 审中-公开
标题翻译：航空发动机空气入口保护系统及相关方法
公开(公告)号：WO2014200590A2
公开(公告)日：2014-12-18
申请号：PCT/US2014/028351
申请日：2014-03-14
申请人： AEROSPACE FILTRATION SYSTEMS, INC.
发明人： BOYCE, Mark, Edward
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/022 , B64D2033/0246 , F02C7/055 , Y02T50/672
摘要： An inlet protection system for filtering air prior to entry into an air intake of an engine of an aircraft includes interchangeably a particle separator panel and a barrier filter panel. The barrier filter panel is adapted to be mounted conformal to the contour of the aircraft and to be interchangeable with the particle separator panel. The particle separator panel has an outer skin and a plurality of particle separators. The outer skin has an opening disposed along a portion of it to discharge filtered particles from within the removable panel directly outward therefrom.
摘要翻译：用于在进入飞行器的发动机的进气口之前过滤空气的入口保护系统可互换地包括颗粒分离器面板和屏障过滤面板。挡板过滤面板适于安装成与飞机的轮廓一致，并可与颗粒分离器板互换。颗粒分离器板具有外皮和多个颗粒分离器。外皮具有沿其一部分设置的开口，以从可移除的面板内直接向外排出过滤的颗粒。

8. 发明申请

WO2008076471A2 AIRCRAFT ENGINE INLET PIVOTABLE BARRIER FILTER 审中-公开
标题翻译：飞机引擎入口可转移障碍物过滤器
公开(公告)号：WO2008076471A2
公开(公告)日：2008-06-26
申请号：PCT/US2007073125
申请日：2007-07-10
申请人： AEROSPACE FILTRATION SYSTEMS I , BELYEW ROBERT R
发明人： BELYEW ROBERT R
IPC分类号： B01D46/10 , B64D33/02 , F02C7/052
CPC分类号： B01D46/10 , B01D2273/10 , B01D2273/14 , B01D2279/60 , B64D33/02 , B64D2033/0246 , F02C7/052 , F05D2220/329
摘要： An inlet barrier filter system for an aircraft engine includes a filter panel including filter media for filtering air prior to intake into the engine. The filter panel has a forward edge. The system further includes an actuator for selectively pivoting the panel to form an opening around the panel for allowing air to bypass the filter. The opening is rearward of the forward edge of the filter panel.
摘要翻译：用于飞机发动机的入口阻挡滤清器系统包括过滤面板，过滤面板包括用于在进入发动机之前过滤空气的过滤介质。过滤面板有一个前缘。该系统还包括用于选择性地枢转面板以在面板周围形成开口以允许空气绕过过滤器的致动器。开口位于过滤板前缘的后方。

9. 发明申请

WO2007016085A1 CONTROL OF ENGINE INTAKE DOOR 审中-公开
标题翻译：发动机入口门控制
公开(公告)号：WO2007016085A1
公开(公告)日：2007-02-08
申请号：PCT/US2006/028831
申请日：2006-07-25
申请人： AEROSPACE FILTRATION SYSTEMS, INC. , STELZER, James, F.
发明人： STELZER, James, F.
IPC分类号： B64D33/02 , F02C7/042
CPC分类号： B64D33/02 , B64D2033/0246 , F02C7/047 , F02C7/05 , Y10T137/0536
摘要： An air induction system for an engine having an improved mechanism for control of an intake door. The system includes a housing having an opening for receiving intake air. A power activated door (56) is pivotable between a closed position wherein the opening is closed and an open position wherein intake air may enter through the opening. Linkages operatively connect an actuator cylinder (62) to the door. The linkages are configured such that movement of the cylinder produces a corresponding rotation of the door which is non-uniform across the cylinder's range of motion. The linkages include first (142) and second (144) bellcranks mounted for pivotal motion, and a link (146) which interconnects the bellcranks. Movement of the cylinder at a first position causes pivoting of the door, while movement at a second position causes substantially no pivoting of the door.
摘要翻译：一种用于具有改进的进气门控制机构的用于发动机的空气感应系统。该系统包括具有用于接收进气的开口的壳体。动力启动门（56）可在闭合位置和关闭位置之间枢转，在该位置中，开口处于关闭位置，而打开位置，其中吸入空气可通过开口进入。连杆将致动器缸（62）可操作地连接到门。连杆构造成使得气缸的运动产生门的相应旋转，其在气缸的运动范围内是不均匀的。连杆包括安装用于枢转运动的第一（142）和第二（144）曲拐，以及连接曲拐的连杆（146）。气缸在第一位置的运动导致门的枢转，而在第二位置的运动基本上不引起门的枢转。

10. 发明申请

WO2015160679A1 ENGINE INLET CONFIGURATION 审中-公开
标题翻译：发动机入口配置
公开(公告)号：WO2015160679A1
公开(公告)日：2015-10-22
申请号：PCT/US2015/025507
申请日：2015-04-13
申请人： SIKORSKY AIRCRAFT CORPORATION
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.
摘要翻译：发动机入口组件包括具有第一入口管道腿部和第二入口管道腿部的入口管道，第一入口管道腿部和第二入口管道腿部朝向位于发动机入口处的公共入口管道出口延伸。第一入口管道腿和第二入口管道腿在空气入口处固定地固定到飞行器的机身上。管道出口具有与发动机入口的浮动接口。

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