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1. 发明授权

US5327744A Integrated environmental control system for a helicopter 失效
标题翻译：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。

2. 发明授权

US6122907A IR suppressor 失效
标题翻译：红外抑制器
公开(公告)号：US6122907A
公开(公告)日：2000-09-26
申请号：US075353
申请日：1998-05-11
申请人： Robert C. Frawley
发明人： Robert C. Frawley
IPC分类号： B64D33/04 , F01N3/02 , F02K1/48 , F02K1/82 , F02K3/04
CPC分类号： F02K1/48 , B64D33/04 , F02K1/825 , Y02T50/671
摘要： An IR Suppressor (20) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) and comprising a primary exhaust manifold (22), first and second mixing ducts (24a, 24b), and a secondary flow shroud (26). More specifically, the primary exhaust manifold (22) includes an elongate duct (28) adapted for receiving a primary flow of the high-temperature engine exhaust from the engine and at least two high aspect ratio nozzles (30a, 30b) integrated in combination with the elongate duct (28). The high aspect ratio nozzles (30a, 30b) are positioned so as to define at least two outlets at the same axial station along the length of the elongate duct (28). The first and second mixing ducts (24a, 24b) are disposed over the high aspect ratio nozzles (30a, 30b) so as to form a mixer/ejector defining at least two ejector inlets (44). The secondary flow shroud (26) is disposed over the mixer/ejector and defines at least one longitudinal inlet (56) disposed in fluid communication with at least one the ejector inlets (44). In operation, the primary flow of engine exhaust is discharged from the high aspect ratio nozzles (30a, 30b) and entrains a secondary flow of ambient air through the longitudinal inlet (56) of the secondary flow shroud (26). The resulting mixed flow is discharged from the IR Suppressor (20) along at least two distinct planes which serve, inter alia, to reduce the envelope of the IR Suppressor (20) while, furthermore, improving suppressor performance.
摘要翻译：一种IR抑制器（20），用于抑制从发动机（12）的高温排气辐射的红外线标记，其包括主排气歧管（22），第一和第二混合管道（24a，24b）和二次流护罩（26）。更具体地，主排气歧管（22）包括细长管道（28），其适于接收来自发动机的高温发动机排气的主流和至少两个高纵横比喷嘴（30a，30b），其与细长管道（28）。高纵横比喷嘴（30a，30b）被定位成在沿着细长管道（28）的长度的同一轴向站处限定至少两个出口。第一和第二混合管道（24a，24b）设置在高纵横比喷嘴（30a，30b）上，以形成限定至少两个喷射器入口（44）的混合器/喷射器。二次流动罩（26）设置在混合器/喷射器上方并且限定至少一个与至少一个喷射器入口（44）流体连通的纵向入口（56）。在操作中，发动机排气的主要流量从高纵横比喷嘴（30a，30b）排出，并且夹带有通过二次流动罩（26）的纵向入口（56）的环境空气的二次流。所产生的混合流量沿着至少两个不同的平面从IR抑制器（20）排出，其特别用于减少IR抑制器（20）的包络，此外改善抑制器性能。

3. 发明授权

US6134879A Suppression system for a gas turbine engine 失效
标题翻译：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。

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