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1. 发明申请

US20180149114A1 LOW INFRARED SIGNATURE EXHAUST THROUGH ACTIVE FILM COOLING ACTIVE MIXING AND ACITVE VANE ROTATION 审中-公开
公开(公告)号：US20180149114A1
公开(公告)日：2018-05-31
申请号：US15365434
申请日：2016-11-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： Joseph Pantalone, III , John S. Chapkovich, III
IPC分类号： F02K1/82 , B64D33/04 , F01D9/04 , F01D17/12 , F01N3/05 , F01D25/30
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , F01D9/041 , F01D17/12 , F01D25/305 , F01N3/05 , F01N2260/022 , F05D2220/323 , F05D2240/128 , F05D2260/202
摘要： An exhaust infrared signature reduction arrangement includes an exhaust duct, a first vane support disposed within the exhaust duct and a second vane support disposed within the exhaust duct downstream from the first vane support. The first vane support and the second vane support are movable between a first configuration and a second configuration.

2. 发明申请

US20180058822A1 SYSTEM AND METHOD OF COORDINATED INFRARED SUPPRESSION AND FLARE LAUNCH 有权
公开(公告)号：US20180058822A1
公开(公告)日：2018-03-01
申请号：US15252850
申请日：2016-08-31
申请人： W.R. DAVIS ENGINEERING LIMITED
发明人： DAVID ANTHONY VAITEKUNAS
IPC分类号： F41H11/02 , F42B4/26
CPC分类号： F41H11/02 , F02K1/825 , F41G7/224 , F41H3/00 , F42B4/26
摘要： Systems and methods are provided that employ an IR suppression system to alter the signature of a vessel during a missile engagement with the objective of confusing a seeker of an incoming missile so as to increase the probability that the seeker is seduced by a flare. The flare is launched and IR suppression is enabled or set to an increased level, with coordinated timing, such that the IR signature of the target vessel is changed at about the same time that the flare is launched.

3. 发明申请

US20140215999A1 AFT EXHAUST SYSTEM FOR ROTARY WING AIRCRAFT 审中-公开
标题翻译：用于旋转式飞机的AFT排气系统
公开(公告)号：US20140215999A1
公开(公告)日：2014-08-07
申请号：US14049735
申请日：2013-10-09
申请人： Joseph Pantalone, III , Ashley DeVito , John S. Chapkovich, III , Steven D. Weiner
发明人： Joseph Pantalone, III , Ashley DeVito , John S. Chapkovich, III , Steven D. Weiner
IPC分类号： B64D33/04
CPC分类号： B64D33/04 , B64C27/04 , B64C27/10 , B64C2027/8236 , B64D2033/045 , F02C7/00 , F02K1/40 , F02K1/825 , F02K3/072
摘要： An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft.
摘要翻译：用于减少旋转翼飞行器的红外发射的排气系统包括具有入口部分和出口部分的管道组件; 所述入口部分构造成从所述飞行器的发动机接收排气; 并且所述出口部分联接到所述入口部分，所述出口部分具有出口管道，所述出口管道具有出口开口，所述出口管道构造成排出了靠近所述旋翼机飞行器尾翼整流罩的排放物。

4. 发明授权

US08661835B2 Bushing for torque load transfer attachment hardware 有权
标题翻译：用于扭矩负载传输附件硬件的衬套
公开(公告)号：US08661835B2
公开(公告)日：2014-03-04
申请号：US12648061
申请日：2009-12-28
申请人： Jorge I. Farah , Jason Hickman , Jose Cintron
发明人： Jorge I. Farah , Jason Hickman , Jose Cintron
IPC分类号： F02C7/20
CPC分类号： F02K1/822 , F02K1/002 , F02K1/04 , F02K1/80 , F02K1/82 , F02K1/825 , F05D2220/328 , F05D2220/90 , F05D2230/64 , F05D2260/30 , Y02T50/671 , Y02T50/675
摘要： A bushing for assembling an exhaust duct liner with an exhaust duct in a gas turbine engine comprises a body, a bushing opening and a first tab. The body is insertable into a duct opening in an exhaust duct. The bushing opening extends through the body to receive a shaft of a liner fastener. The first tab protrudes from the body to extend into an interior of the duct to prevent rotation of a head of the liner fastener.
摘要翻译：用于在燃气涡轮发动机中组装具有排气管道的排气管道衬套的衬套包括主体，衬套开口和第一突出部。身体可插入排气管道中的管道开口中。衬套开口延伸穿过主体以接纳衬垫紧固件的轴。第一突片从主体伸出以延伸到管道的内部，以防止衬套紧固件的头部旋转。

5. 发明申请

US20100146980A1 MASKING ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机的掩蔽装置
公开(公告)号：US20100146980A1
公开(公告)日：2010-06-17
申请号：US12600262
申请日：2007-05-22
申请人： Linda Ström , Hans Martensson , Jonas Larsson , Lena Andersson
发明人： Linda Ström , Hans Martensson , Jonas Larsson , Lena Andersson
IPC分类号： F02K1/82
CPC分类号： F02K1/825 , F02K3/10 , Y02T50/671
摘要： A masking arrangement for a gas turbine engine includes a plurality of annular elements arranged overlapping one another when these are viewed in an axial direction so as to mask at least a substantial portion of any interior hot and rotating gas turbine engine part at an aft end of the gas turbine engine from rear view when the masking arrangement is applied downstream the interior part in the gas turbine engine.
摘要翻译：用于燃气涡轮发动机的掩蔽装置包括当沿轴向方向观察时重叠的多个环形元件，以便在至少大部分的内部热转动燃气涡轮发动机部件的至少一部分当在燃气涡轮发动机的内部部分的下游施加掩蔽装置时，后视图的燃气涡轮发动机。

6. 发明授权

US07721522B2 Torque load transfer attachment hardware 有权
标题翻译：扭矩负载传输附件硬件
公开(公告)号：US07721522B2
公开(公告)日：2010-05-25
申请号：US11514293
申请日：2006-08-31
申请人： Jorge I. Farah , Jason Hickman , Jose Cintron
发明人： Jorge I. Farah , Jason Hickman , Jose Cintron
IPC分类号： F02C7/00
CPC分类号： F02K1/822 , F02K1/002 , F02K1/04 , F02K1/80 , F02K1/82 , F02K1/825 , F05D2220/328 , F05D2220/90 , F05D2230/64 , F05D2260/30 , Y02T50/671 , Y02T50/675
摘要： A bushing for assembling an exhaust duct liner with an exhaust duct in a gas turbine engine comprises a body, a bushing opening and a first tab. The body is insertable into a duct opening in an exhaust duct. The bushing opening receives a shaft of a liner fastener, wherein the fastener is connectable with a duct liner. The first tab extends into the duct opening and prevents rotation of the liner fastener.
摘要翻译：用于在燃气涡轮发动机中组装具有排气管道的排气管道衬套的衬套包括主体，衬套开口和第一突出部。身体可插入排气管道中的管道开口中。衬套开口接收衬垫紧固件的轴，其中紧固件可与导管衬套连接。第一突片延伸到管道开口中并且防止衬垫紧固件的旋转。

7. 发明申请

US20100074736A1 Thermal management system 有权
标题翻译：热管理系统
公开(公告)号：US20100074736A1
公开(公告)日：2010-03-25
申请号：US12284391
申请日：2008-09-22
申请人： Larry Allen Junod
发明人： Larry Allen Junod
IPC分类号： F02C7/141 , F02C9/18 , F02C3/32
CPC分类号： F02C7/14 , F02C3/32 , F02K1/825 , F05D2260/601 , F41A13/10 , F41H13/0043 , Y02T50/675
摘要： In one embodiment a gas turbine engine is disclosed having a heat exchanger at least partially disposed in a bypass duct. In one form the gas turbine engine is a high bypass ratio engine. The heat exchanger may be coupled with a directed energy weapon to provide coolant flow and regulate the temperature of the directed energy weapon. Other devices may also be coupled with the heat exchanger, either as an alternative to in addition to the directed energy weapon.
摘要翻译：在一个实施例中，公开了一种具有至少部分地布置在旁路管道中的热交换器的燃气涡轮发动机。在一种形式中，燃气涡轮发动机是高旁路比发动机。热交换器可以与定向能量武器联接以提供冷却剂流动并调节定向能量武器的温度。除了定向能量武器之外，其它装置也可以与热交换器耦合，作为替代。

8. 发明申请

US20090317243A1 HIGH REFLECTIVITY INFRARED COATING APPLICATIONS FOR USE IN HIRSS APPLICATIONS 审中-公开
标题翻译：高反射率红外涂层应用在HIRSS应用中的应用
公开(公告)号：US20090317243A1
公开(公告)日：2009-12-24
申请号：US11743303
申请日：2007-05-02
申请人： Andrew Jay SKOOG , Jane Ann MURPHY , John Michael JASANY , Mariah Dawn SENTER
发明人： Andrew Jay SKOOG , Jane Ann MURPHY , John Michael JASANY , Mariah Dawn SENTER
IPC分类号： F02C7/24
CPC分类号： F02K1/825 , B32B15/018 , C22C19/055 , C23C24/08 , C23C26/00 , C23C30/00 , F05D2230/90 , F05D2300/611 , Y10T428/12771 , Y10T428/12806 , Y10T428/12861 , Y10T428/12875
摘要： The present invention is a hover infrared suppression system for a gas turbine engine comprising a hover infrared suppression system having an upstream first stage, a second stage downstream of the first stage and a third stage downstream of the second stage, the engine operating at a temperature sufficient to cause the hover infrared suppression system to emit infrared radiation. The present invention further comprises a high reflectivity coating applied over a preselected area of at least one of the stages of the hover infrared suppression system to reduce the infrared radiation emitted from the engine, the high reflectivity coating being fired after application.
摘要翻译：本发明是一种用于燃气涡轮发动机的悬浮式红外线抑制系统，其包括具有上游第一级，第一级下游的第二级和第二级下游的第三级的悬停红外线抑制系统，发动机在温度足以使悬停的红外线抑制系统发射红外辐射。本发明还包括施加在悬浮红外线抑制系统的至少一个级的预选区域上的高反射率涂层，以减少从发动机发射的红外辐射，施加后高反射率涂层被烧制。

9. 发明申请

US20080236138A1 Arrangement for Propelling an Aircraft, Aircraft and Outlet Nozzle for a Jet Engine 失效
标题翻译：用于推进喷气发动机的飞机，飞机和出口喷嘴的安排
公开(公告)号：US20080236138A1
公开(公告)日：2008-10-02
申请号：US12067112
申请日：2005-09-27
申请人： Bernhard Gustafsson
发明人： Bernhard Gustafsson
IPC分类号： F02K3/02
CPC分类号： B64D33/04 , F02K1/40 , F02K1/825 , F05D2250/14 , F05D2260/20 , Y02T50/672 , Y02T50/675
摘要： The invention relates to an arrangement for propelling an aircraft comprising a jet engine and an outlet nozzle arranged downstream of the jet engine. The jet engine is of a type which generates an internal core flow and an external fan flow. A part of the outlet nozzle has an internal surface which defines a gas duct for the fan flow. The aforementioned part of the outlet nozzle includes a wall structure that is arranged at a distance from the internal surface such that it separates the gas duct for the fan flow from an internal gas duct for the core flow.
摘要翻译：本发明涉及一种用于推进飞机的装置，其包括喷气发动机和布置在喷气发动机下游的出口喷嘴。喷气式发动机是产生内部气流和外部风扇流的类型。出口喷嘴的一部分具有限定用于风扇流动的气体管道的内表面。出口喷嘴的上述部分包括壁结构，该壁结构设置在距离内表面一定距离处，使得其将用于风扇流的气体管道与用于芯流的内部气体管道分离。

10. 发明申请

US20070227132A1 PASSIVE EXHAUST SUPPRESSOR AND METHOD 有权
标题翻译：被动排气抑制剂和方法
公开(公告)号：US20070227132A1
公开(公告)日：2007-10-04
申请号：US11760097
申请日：2007-06-08
申请人： James Means
发明人： James Means
IPC分类号： F01N3/00
CPC分类号： F01N13/082 , F02K1/825
摘要： A passive exhaust system is described that provides effective infrared signature suppression without affecting radar cross-section while maintaining stable function in crosswinds. A passive exhaust system may include an array of ducts with each duct having a primary and secondary nozzle. Central ducts draw in ambient cooling air to create a thick cooling film along exterior surfaces and cause plume dilution, stabilize the plume flow in a crosswind, and prevent heating of visible surfaces. Visible surfaces may incorporate radar absorbing materials and may be inclined at an angle or fabricated with a diffuse surface to prevent specular reflection. Visible surfaces may be constructed from or covered with low infrared emissivity materials. A variable passive flow controller ensures a sufficient velocity exhaust flow.
摘要翻译：描述了一种无源排气系统，可在不影响雷达横截面的同时提供有效的红外特征抑制，同时保持侧风中的稳定功能。无源排气系统可以包括管道阵列，每个管道具有主喷嘴和次喷嘴。中央管道吸入环境冷却空气，以沿着外部表面产生厚的冷却膜，并引起羽流稀释，在侧风中稳定羽流，并防止可见表面的加热。可见表面可以包括雷达吸收材料，并且可以以一定角度倾斜或用扩散表面制造以防止镜面反射。可见表面可由低红外辐射材料构成或覆盖。可变的被动流量控制器确保足够的速度排气流量。

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