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    Low observable engine inlet system
    3.
    发明授权
    Low observable engine inlet system 失效
    低可观察的发动机进气系统

    公开(公告)号：US5694763A

    公开(公告)日：1997-12-09

    申请号：US507686

    申请日：1990-04-11

    申请人： Armand F. Amelio ,  Richard S. Barnard ,  James J. Manzolli

    发明人： Armand F. Amelio ,  Richard S. Barnard ,  James J. Manzolli

    IPC分类号： B64D33/02 ,  F02C7/042 ,  F02C7/047 ,  F02C7/05 ,  F02C7/055

    CPC分类号： F02C7/05 ,  B64D33/02 ,  F02C7/042 ,  F02C7/047 ,  B64D2033/0286 ,  Y02T50/671 ,  Y10T137/0645

    摘要： A turbine engine inlet system includes a curved duct 14 to deliver air to the engine, an inlet lip 16 to smooth the entry of air flowing into the duct, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is flush with the forward inlet section 18 during normal flight conditions and extended to slightly above the inlet lip 16 during icing conditions.

    摘要翻译： 涡轮发动机入口系统包括用于将空气输送到发动机的弯曲管道14，用于平滑流入管道的空气进入的入口唇缘16，浸没在飞机皮肤轮廓内的前进入部分18，以提供一定程度的柱塞恢复 以及可移动的空气导流板20，其在正常飞行条件期间与前进入部分18齐平并且在结冰条件期间延伸到略高于入口唇缘16的上方。

    Suppression system for a gas turbine engine
    4.
    发明授权
    Suppression system for a gas turbine engine 失效
    燃气轮机的抑制系统

    公开(公告)号：US6134879A

    公开(公告)日：2000-10-24

    申请号：US454167

    申请日：1989-12-21

    申请人： Robert C. Frawley ,  Armand F. Amelio ,  Richard S. Barnard

    发明人： Robert C. Frawley ,  Armand F. Amelio ,  Richard S. Barnard

    IPC分类号： B64D33/04 ,  F02K1/82 ,  F02K1/44

    CPC分类号： B64D33/04 ,  F02K1/825 ,  Y02T50/672

    摘要： A suppression system for a gas turbine engine uses a tapered exhaust manifold with a plurality of exhaust nozzles acting in conjunction with a plurality of mixing cells to produce cooling of an exhaust gas stream upon exit from an aircraft. The cooling air is supplied to the mixing cells in such a way that the walls of the cells are inherently maintained at a desired temperature without the use of dedicated cooling apparatus such as finned head exchangers, film cooling slots, etc. This approach allows the typically conflicting requirements of low IR signature and low radar cross section to be simultaneously satisfied in an efficient, light weight and low cost manner. The exhaust gas suppression system is preferably disposed in the tail section of a helicopter aircraft, having nozzles pointing in an essentially downward direction to reduce the threat from an over flying aircraft while minimizing the ability of ground based systems to acquire a direct line of sight on any hot surfaces or to detect the exhaust cavity using radar.

    摘要翻译： 用于燃气涡轮发动机的抑制系统使用具有多个排气喷嘴的锥形排气歧管，多个排气喷嘴与多个混合室结合起来，以在从飞机出来时产生排气流的冷却。 将冷却空气以这样的方式供应到混合室，使得电池的壁固有地保持在期望的温度，而不使用专用冷却装置，例如翅片式头部交换器，薄膜冷却槽等。这种方法允许通常 低IR签名和低雷达横截面的冲突要求以有效，重量轻，成本低的方式同时满足。 排气抑制系统优选地设置在直升机飞行器的尾部中，其具有指向基本上向下的方向的喷嘴，以减少来自飞行飞行器的威胁，同时使基于地面的系统获得直接视线的能力最小化 任何热表面或使用雷达检测排气腔。

    Fuel intake device for fuel systems
    5.
    发明授权
    Fuel intake device for fuel systems 失效
    燃油系统燃油进气装置

    公开(公告)号：US5776341A

    公开(公告)日：1998-07-07

    申请号：US772679

    申请日：1996-12-23

    申请人： Richard S. Barnard ,  Scott A. Chasen

    发明人： Richard S. Barnard ,  Scott A. Chasen

    IPC分类号： F02M37/10 ,  B01D29/11 ,  B01D35/02 ,  B01D35/027 ,  B01D35/147 ,  F02M37/22

    CPC分类号： B01D35/027 ,  B01D29/114

    摘要： A fuel intake device (20) for a fuel system (10) having a fuel tank (14) for containing a supply of fuel (16) and an internal fuel feed line (18) which is disposed internally of the fuel tank (14) and which extends into a sump region (26) thereof. The fuel intake device (20) is characterized by a filter assembly (40) which envelopes an end portion (18.sub.E) of the internal fuel feed line (18) and which includes a lower fuel filtering portion (42) and an upper fuel bypass portion (44). The lower fuel filtering portion (42) has a plurality of fine apertures (42.sub.O) therein for facilitating a primary flow (P.sub.F) of fuel (16) therethrough and for filtering debris from the supply of fuel (16) in a normal operating mode. The upper fuel bypass portion (44) has a plurality of coarse apertures (44.sub.O) for facilitating a secondary flow (S.sub.F) of fuel therethrough in a bypass operating mode. Furthermore, the filter assembly (40) is situated about the end portion (18.sub.E) such that the inlet orifice (18.sub.O) thereof is disposed internally of the lower fuel filtering portion (42) and such that the coarse apertures (44.sub.O) of the upper bypass portion (44) are distally spaced from the inlet orifice (18.sub.O). The fuel intake device is further characterized by a shroud member (50) disposed about the filter assembly (40), which shroud member (50) includes an upper end portion (52) disposed in sealed combination with an external peripheral surface (18.sub.P) of the internal fuel feed line (18) and a lower end portion (54) which extends into the sump region (26) of the fuel tank (14). The lower end portion (54), furthermore, defines an opening for facilitating fuel flow to the filter assembly (40).

    摘要翻译： 一种用于燃料系统（10）的燃料进入装置（20），其具有用于容纳燃料供应的燃料箱（14）和设置在所述燃料箱（14）内部的内部燃料供给管线（18） 并且其延伸到其中的贮槽区域（26）中。 燃料进入装置（20）的特征在于包围内部燃料供给管线（18）的端部（18E）的过滤器组件（40），其包括下部燃料过滤部分（42）和上部燃料旁路部分 （44）。 下部燃料过滤部分（42）在其中具有多个细孔（42O），用于促进燃料（16）的主流（PF）通过其中并用于以正常操作模式从燃料供应源16过滤碎屑。 上部燃料旁路部分（44）具有多个粗略孔（44O），用于在旁路操作模式中促进燃料的二次流（SF）。 此外，过滤器组件40围绕端部部分18E设置成使得其入口孔口18O设置在下部燃料过滤部分42的内部，并且使得上部的上部的粗略孔44O） 旁路部分（44）与入口孔（180）远离间隔开。 燃料进入装置的特征还在于围绕过滤器组件（40）设置的护罩构件（50），所述护罩构件（50）包括与外部外围表面（18P）密封组合设置的上端部分（52） 内部燃料供给管线（18）和延伸到燃料箱（14）的集油槽区域（26）中的下端部分（54）。 此外，下端部分（54）限定用于促进燃料流向过滤器组件（40）的开口。

    Integrated environmental control system for a helicopter
    6.
    发明授权
    Integrated environmental control system for a helicopter 失效
    直升机综合环境控制系统

    公开(公告)号：US5327744A

    公开(公告)日：1994-07-12

    申请号：US992392

    申请日：1992-12-18

    申请人： Robert C. Frawley ,  Thomas Perrotta ,  Richard S. Barnard

    发明人： Robert C. Frawley ,  Thomas Perrotta ,  Richard S. Barnard

    IPC分类号： B01D50/00 ,  B01D51/00 ,  B64D20060101 ,  B64D13/00 ,  B64D13/04 ,  B64D13/08 ,  F22D20060101 ,  F25B9/00 ,  F25D9/00

    CPC分类号： B64D13/04 ,  B64D13/08 ,  B64D2013/0614 ,  B64D2013/0651 ,  B64D2013/0662 ,  F25B9/004 ,  Y02T50/44 ,  Y02T50/56 ,  Y10S62/05

    摘要： A compact, lightweight integrated environmental control (IEC) system for a helicopter incorporates in operative combination an environmental control system (ECS) and a nuclear/biological/chemical life support system (NBC LSS). The IEC system includes a refrigerant subsystem, a regenerative heat exchange apparatus, a decontamination subsystem, and an airflow distribution network, and is operative to provide super-cooled, super-dry, decontaminated airflow, in seriatim, directly to left and right mission equipment package bays and the cockpit for cooling of avionics/electronic modules and crew comfort. The IEC system is further operative to directly provide cooled, super-dry, decontaminated airflow for cooling of avionics/electronic modules of the mid mission equipment package bay and for over pressurizing the left and right mission equipment package bays to preclude contaminant infiltration thereof.

    摘要翻译： 用于直升机的紧凑轻便的综合环境控制（IEC）系统结合了环境控制系统（ECS）和核/生物/化学生命维持系统（NBC LSS）。 IEC系统包括制冷剂子系统，再生热交换装置，净化子系统和气流分配网络，并且可操作地提供超冷却，超干燥的净化空气流，直接向左右任务设备 包装舱和驾驶舱，用于冷却航空电子/电子模块和船员舒适。 IEC系统进一步操作，直接提供冷却，超干燥，净化的气流，用于冷却中间任务设备包装舱的航空电子设备/电子模块，以及过度加压左右任务设备包装舱，以防止其污染物渗透。