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111. 发明授权

US4566270A Gas turbine engine infra-red radiation suppressor 失效
标题翻译：燃气轮机引擎红外辐射抑制器
公开(公告)号：US4566270A
公开(公告)日：1986-01-28
申请号：US671336
申请日：1984-11-14
申请人： John R. Ballard , Peter H. Timmis , Michael J. Buller
发明人： John R. Ballard , Peter H. Timmis , Michael J. Buller
IPC分类号： F41H3/00 , B64D33/04 , F02K1/36 , F02K1/46 , F02K1/82 , F41H11/02 , F02C7/18
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , Y02T50/67 , Y02T50/672
摘要： A gas turbine engine infra-red radiation suppressor comprising an exhaust nozzle which is surrounded by a duct having a plurality of diffuser vanes at its downstream end. The exhaust nozzle and duct constitute an ejector which is powered by the exhaust efflux from the exhaust nozzle and draws ambient air into the duct through a gap between the exhaust nozzle and the duct. The air serves to cool the exhaust efflux and thereby reduce its infra-red radiation emission, and the diffuser vanes prevent direct line of sight of the hot exhaust nozzle.
摘要翻译：一种燃气涡轮发动机红外辐射抑制器，包括排气喷嘴，该排气喷嘴在其下游端由具有多个扩散器叶片的管道包围。排气喷嘴和管道构成喷射器，其由从排气喷嘴排出的排气提供动力，并且通过排气喷嘴和管道之间的间隙将环境空气吸入管道。空气用于冷却排气流，从而减少其红外辐射发射，并且扩散器叶片防止热排气喷嘴的直接视线。

112. 发明授权

US4537026A Variable area nozzles for turbomachines 失效
标题翻译：用于涡轮机的可变区域喷嘴
公开(公告)号：US4537026A
公开(公告)日：1985-08-27
申请号：US654520
申请日：1984-09-25
申请人： Douglas J. Nightingale
发明人： Douglas J. Nightingale
IPC分类号： F02K1/08 , F02K1/82 , B64D33/04
CPC分类号： F02K1/825 , F02K1/08
摘要： Jet propulsion powerplant comprising a gas producer 11 having a first flow duct 12 for receiving the output of the gas producer 11. The flow duct 12 includes a nozzle 13 having a center body 16 which has an upstream part 17 and a downstream part 20. Motors 22 are provided for expanding and contracting the downstream part 20 relative to the upstream part 17. A second flow duct 33 having an inlet 30 openable to airflow and connected to the interior of said upstream part 17 is provided. An outlet 24 from the interior of the upstream part 17, is provided at the downstream end of the upstream part 17. The outlet 24 opens into the interior of the first flow duct 12 by contracting the downstream part 20 relative to the upstream part 17. By such an arrangement, infrared radiation may be suppressed when necessary by opening the inlet for air flow and controlling the upstream and downstream parts so that there can be a mixing of air with exhaust gases which reduces the mean temperature of the exhaust gases.
摘要翻译：喷气推进动力装置包括具有用于接收气体生成器11的输出的第一流动管道12的气体生成器11.流动管道12包括具有中心体16的喷嘴13，该中心体具有上游部分17和下游部分20。 22设置成用于相对于上游部分17使下游部分20膨胀和收缩。具有能够流动并连接到所述上游部分17的内部的入口30的第二流动管道33被设置。来自上游部分17的内部的出口24设置在上游部分17的下游端。通过使下游部分20相对于上游部分17收缩，出口24打开到第一流动管道12的内部。通过这样的布置，通过打开用于空气流动的入口并控制上游和下游部分，可以在必要时抑制红外辐射，使得可以将空气与排气混合，这降低了排气的平均温度。

113. 发明授权

US4335573A Gas turbine engine mixer 失效
标题翻译：燃气轮机发动机搅拌机
公开(公告)号：US4335573A
公开(公告)日：1982-06-22
申请号：US78333
申请日：1970-09-02
申请人： Jack D. Wright
发明人： Jack D. Wright
IPC分类号： F02K1/38 , F02K1/82 , F02K3/10 , F02K3/04
CPC分类号： F02K1/386 , F02K1/825
摘要： An afterburning turbofan engine includes amixer for mixing the engine generated hot gas and fan streams prior to discharge through the engine nozzle. The mixer includes a fixed upstream portion and a movable downstream portion which may be indexed to selectively interchange flow communication between the chutes of the two portions to effect a temperature reduction in the downstream mixer portion and, hence, a reduction in infrared radiation.
摘要翻译：后燃烧涡轮风扇发动机包括用于在发动机喷嘴排出之前混合发动机产生的热气体和风扇流的混合器。混合器包括固定的上游部分和可移动的下游部分，可移动的下游部分可以被转位以选择性地交换两部分的滑槽之间的流动连通，以在下游混合器部分中实现温度降低，并因此降低红外辐射。

114. 发明授权

US4295332A Infrared suppressor system 失效
标题翻译：红外线抑制系统
公开(公告)号：US4295332A
公开(公告)日：1981-10-20
申请号：US960351
申请日：1978-11-13
申请人： William Steyer , Robert J. Duffy
发明人： William Steyer , Robert J. Duffy
IPC分类号： F02C7/00 , B64D33/04 , F02K1/28 , F02K1/82 , F02K3/00 , F02K7/00
CPC分类号： B64D33/04 , F02K1/825 , B64D2033/045
摘要： An infrared suppressor system for gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine.
摘要翻译：提供了一种用于燃气轮机的红外抑制器系统，用于抑制与发动机的热金属部件和从发动机排出的热废气相关联的红外辐射。

115. 发明授权

US4215537A Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine 失效
标题翻译：用于抑制从燃气涡轮发动机发射的红外辐射的装置和方法
公开(公告)号：US4215537A
公开(公告)日：1980-08-05
申请号：US928446
申请日：1978-07-27
申请人： John F. Hurley
发明人： John F. Hurley
IPC分类号： B64D33/04 , F02K1/82 , F02C7/18 , F02K1/26
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , Y02T50/671
摘要： An apparatus for and method of suppressing infrared radiation emitted from hot metal parts at the aft end of a gas turbine engine and from the exhaust gas plume thereof are provided and such apparatus comprises a dual purpose ejector vane assembly operatively associated with the engine for introducing cooling ambient air into the hot engine exhaust gases and hiding the hot metal parts wherein the assembly comprises a tubular duct structure comprised of two cooperating portions defined by an upstream portion and a downstream portion with the upstream portion having a discharge end of a particular area and the downstream portion having an inlet end provided with an inlet area which is larger than the particular area to define an annular space therebetween for receiving cooling ambient air therethrough by ejector action during operation of the engine, and one of the portions has at least one vane providing at least one stream of cooling ambient air by ejector action completely across the duct structure which serves to break the exhaust gases confined thereby into a plurality of separate exhaust gas streams and provide mixing of the one stream with the exhaust gases completely across the duct structure and wherein the assembly provides a substantial amount of cooling ambient air with maximum air film cooling of metal parts of the assembly and maximum dilution of the exhaust gas plume for a minimum infrared signal.
摘要翻译：提供了一种用于抑制从燃气涡轮发动机的后端处的热金属部件和其排气羽流发射的红外辐射的装置和方法，并且这种装置包括与发动机可操作地相关联的用于引入冷却的双重目的的喷射器叶片组件环境空气进入热发动机废气并隐藏热金属部件，其中组件包括管状管道结构，管状管道结构包括由上游部分和下游部分限定的两个协作部分，其中上游部分具有特定区域的排放端，下游部分具有入口端，其具有大于特定区域的入口区域，以限定其间的环形空间，用于在发动机操作期间通过喷射器作用接收通过其中的冷却环境空气，并且其中一个部分具有至少一个叶片，至少一个冷却环境空气的流通过喷射器动作完全穿过管道结构，其用于将由此限制的废气分解成多个分离的排气流，并且将一个流与排气完全混合穿过管道结构，并且其中组件提供大量的具有最大空气的大量冷却环境空气组件的金属部件的薄膜冷却和最小的红外信号的废气羽流的最大稀释。

116. 发明授权

US4099375A Exhaust plume reduction and cooling system 失效
标题翻译：尾气减排和冷却系统
公开(公告)号：US4099375A
公开(公告)日：1978-07-11
申请号：US765500
申请日：1977-02-03
申请人： Clinton F. Inglee
发明人： Clinton F. Inglee
IPC分类号： F02K1/82 , F02C7/18
CPC分类号： F01N13/082 , F02K1/825 , F01N2260/06 , Y02T50/672
摘要： A radiation suppressor for exhaust turbine or other engines which signifitly reduces the lock-on range of infrared seeking missiles is provided. Engine exhaust gases are the sole power source for driving an exhaust turbine which includes a self-contained turbo-fan assembly and a surrounding plenum-shroud assembly both of which are structurally supported by the aircraft or other vehicle-cooling air duct assembly. The turbo-fan assembly comprises a turbine wheel having a top or outer fan for providing both hot metal and plume cooling air and a central centrifugal blower to partially cool the hollow turbine blades. The duct assembly is combined with ambient air passages to distribute plume cooling air, while a plenum-shroud assembly which surrounds these assemblies includes internally cooled radial vanes disposed in a turbine shroud as well as an outer fairing having flow passages for cooling air.
摘要翻译：提供了一种用于排气涡轮或其他发动机的辐射抑制器，其显着地减少了寻找红外线的导弹的锁定范围。发动机废气是用于驱动排气涡轮机的唯一动力源，其包括独立涡轮风扇组件和周围的增压室 - 护罩组件，两者均由结构上由飞行器或其它车辆冷却风道组件支撑。涡轮风扇组件包括具有用于提供热金属和羽流冷却空气的顶部或外部风扇的涡轮机叶轮和用于部分地冷却中空涡轮机叶片的中央离心式鼓风机。管道组件与环境空气通道组合以分布羽流冷却空气，而围绕这些组件的增压室罩组件包括设置在涡轮机罩中的内部冷却的径向叶片以及具有用于冷却空气的流动通道的外部整流罩。

117. 发明授权

US4018046A Infrared radiation suppressor for gas turbine engine 失效
标题翻译：燃气轮机的红外辐射抑制器
公开(公告)号：US4018046A
公开(公告)日：1977-04-19
申请号：US596593
申请日：1975-07-17
申请人： John F. Hurley
发明人： John F. Hurley
IPC分类号： B64D33/04 , F02K1/82 , F02C7/18 , F02C7/24
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045
摘要： Apparatus for suppressing infrared radiation emitted from hot metal parts at the aft end of a gas turbine engine and from the exhaust gas plume thereof is provided and such apparatus employs components which utilize an ejector principle to provide cooling action utilizing ambient air and such components may be provided with means for adjustment thereof to vary the amount of cooling ambient air.
摘要翻译：提供了一种用于抑制从燃气涡轮发动机的后端处的热金属部件和其废气羽流发射的红外辐射的装置，并且这种装置使用利用喷射器原理来利用环境空气提供冷却作用的部件，并且这些部件可以是设置有用于调节其以改变冷却环境空气的量的装置。

118. 发明授权

US4007587A Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine 失效
标题翻译：用于抑制从燃气涡轮发动机发射的红外辐射的装置和方法
公开(公告)号：US4007587A
公开(公告)日：1977-02-15
申请号：US633226
申请日：1975-11-19
申请人： Clifford R. Banthin , Gary W. Decko , John F. Hurley
发明人： Clifford R. Banthin , Gary W. Decko , John F. Hurley
IPC分类号： B64D33/04 , F02K1/82 , F02K1/02 , F02K1/26
CPC分类号： B64D33/04 , F02K1/825 , B64D2033/045
摘要： An apparatus for and method of suppressing infrared radiation emitted from hot metal parts at the aft end of a gas turbine engine and from the exhaust gas plume thereof is provided and such apparatus comprises a dual purpose ejector vane assembly operatively attached to the engine for introducing cooling ambient air into the hot engine exhaust gases and hiding the hot metal parts. The vane assembly has a duct structure for receiving and confining the engine exhaust gases and the assembly provides at least one stream of cooling ambient air across one full dimension of the duct structure and exhaust gases confined thereby with the stream of cooling ambient air mixing with the hot engine exhaust gases across the full dimension of the duct structure to assure optimum mixing thereof.
摘要翻译：提供了一种用于抑制从燃气涡轮发动机的后端处的热金属部件和其排气羽流发射的红外辐射的装置和方法，并且这种装置包括可操作地附接到发动机的双重目的的喷射器叶片组件，用于引导冷却环境空气进入热机排气并隐藏热金属部件。叶片组件具有用于接收和限制发动机废气的管道结构，并且该组件提供至少一个冷却环境空气流，所述冷却环境空气流过管道结构的一个整个尺寸，并且由此限制的排气与冷却环境空气流混合，热管道结构的整个尺寸的热发动机废气，以确保其最佳混合。

119. 发明授权

US4004416A Infra-red suppressor for use with turbo-shaft engine 失效
标题翻译：用于涡轮轴发动机的红外线抑制器
公开(公告)号：US4004416A
公开(公告)日：1977-01-25
申请号：US19576
申请日：1970-03-16
申请人： Armand F. Amelio , Kenneth M. Rosen
发明人： Armand F. Amelio , Kenneth M. Rosen
IPC分类号： F02K1/82 , F02K3/04
CPC分类号： F02K1/825
摘要： An infra-red radiation suppressor adapted to be positioned to alter the flow of the exhaust gases of a turbo-shaft engine and sized to block view into the engine outlet and including self-pumping ejector means to cool the visible surfaces of the suppressor.BACKGROUND OF THE INVENTION1. Field of InventionThis invention relates to infra-red radiation suppression and more particularly to an infra-red radiation suppressor which is adapted to be mounted to block the view into the outlet of a turbo-shaft engine and to intercept and alter the flow of exhaust gases thereof and which includes self-pumping ejector mechanisms to provide cooling of the exposed suppressor parts.2. Description of the Prior ArtDuring military combat it is common practice to utilize infra-red radiation seeking missiles and other destructive vehicles to seek out and destroy upon contact military flight vehilces which use propulsion mechanisms, such as turbo-jet or turbo-shaft engines or rockets, which operate at a sufficiently high temperature that the metal parts thereof emit significant infra-red radiation. The radiation emitted by the exhaust gases is largely attenuated by the atmosphere. In any case it has been found to be of less significance than that emitted by the exposed metal parts.The infra-red radiation threat is fully described in U.S. Pat. No. 3,210,934, to which reference may be made.Protection against this threat is accomplished by blocking the view into the engine outlet to prevent the infra-red radiation seeking devices from detecting the infra-red radiation emitting parts therewithin and by cooling exposed parts to prevent them from reaching the critical infra-red radiation emitting temperature which can be detected by the oncoming missile.In the prior art, such as in U.S. Pat. No. 3,210,934, this exposed part cooling function is performed by apparatus which either needs a pressure source for the cooling fluid or which is ram-air responsive. The disadvantage of such systems is that devices which require pressure sources for providing pressurized cooling fluid to the exposed vehicle parts either require a separate pumping source with its attendant added weight and complication to the flight vehicle system, or require that pressurized engine compressor bleed air be utilized for this purpose, thereby reducing the power generating capability of the engine so bled. The devices which are ram-air responsive must not only be capable of being positioned so that some part thereof is in impinging contact with atmosphere to develop the ram-air effect, and this is not possible or practical in power generating devices which are positioned internally within the flight vehicle and, further, such ram-air responsive devices are inoperative when the flight vehicle is not moving forward at a substantial velocity. Accordingly, such ram-air responsive devices could not be utilized if the flight vehicle were a helicopter, which is capable of operating in many directions other than forward and which is further capable of operating in the hover mode, which mode is very important in many military situations.It will therefore be seen that the prior art devices either add weight and complication to the overall system when a separate cooling fluid power source is utilized, or reduce the engine power generating capability when an engine generated pressure source, such as turbo-jet or turbo-shaft compressor, is bled to provide this cooling fluid. Further, ram responsive infra-red radiation suppressors are ineffective on helicopters during flight modes other than forward flight and the all-important military hover mode.In addition, it has been suggested in the prior art that infra-red radiation suppressor parts be made completely porous so as to be able to use transpiration cooling, that is, the forced passage of cooling air through the various pores in the suppressor wall members. While transpiration cooling is accepted as an efficient method of cooling from a theoretical thermodynamic standpoint, film cooling is only slightly less efficient and has many advantages. Transpiration cooling is particularly unsuited for helicopter operation. The helicopter often lands and takes-off from unprepared areas and foreign matter, including dust and debris, fill the air and are injected into the engine and pass therefrom into the suppressor. The debris will attempt to pass with the air through the small 40 micron pores of the transpiration cooled suppressor members, thereby clogging these pores with foreign matter. With transpiration cooling, even if a complete clogging of all the pores is not encountered, localized infra-red radiating hot spots in the walls would be encountered in the localized clogged portions. In helicopter use, an attempt to keep the pores of a transpiration cooled suppressor absolutely clean in service would present very substantial maintenance problems. A further disadvantage of transpiration cooling is that the porous parts involved cannot be fabricated by conventional methods, as can the solid sheet metal parts of our suppressor. In addition, in a transpiration cooled system, it would be necessary, in some suppressor stations, to be discharging cooling air into a high static pressure region, and this would require the use of a positive pressure source. Still further, the partially clogged pores, or the partially clogged porous wall, offers increased resistance to cooling air flow therethrough and hence a greater positive pressure is required to cause the cooling air to pass through these restricted pores, therefore, transpiration cooling produces the undersirable need of an extremely high capacity pressure source capable of generating high pressure. To complicate the problem, we are not able to produce an even cooling effect over the entire surface of the suppressor due to irregular pore clogging problems. Contrary to the clogging problems presented by the transpiration cooled suppressor, the ejector slots of our suppressor are sufficiently large that they are not subject to clogging.In addition, the prior art has taught infra-red radiation prevention by passing cooling air between closely positioned double walls of the suppressor parts to produce convection cooling thereof. Since there is substantial resistance to the flow of cooling air between two closely spaced walls of this type, very substantial air pressure is required to cause the air to flow therethrough with sufficient velocity to effectively cool the passage defining parts.Contrary to the transpiration cooling and the convection cooling of the prior art, we are using primarily film cooling. Since film cooling produces a cooling air film between the suppressor parts and the hot exhaust gases to prevent heating of the suppressor parts, less air is used in such a system because it requires less air to prevent heating of suppressor parts by film cooling than it does to convectively cool suppressor parts which are directly scrubbed by the hot exhaust gases.SUMMARY OF THE INVENTIONA primary object of the present invention is to provide an infra-red radiation suppressor for use with a turbine engine, such as a turbo-shaft engine, which both blocks view into the outlet of the turbine engine from all vantage points, which is mounted independently of the engine so as not to change the operating characteristics thereof and so as to be free from absorbing the vibrations and physical distortion therefrom, which includes no moving parts, and which includes a self-pumping, passive cooling system for the exposed suppressor parts to prevent them from reaching critical infra-red radiation emitting temperatures.In accordance with the present invention, an infra-red radiation suppressor is provided for use with a flight vehicle which is operable during all modes of operation of the flight vehicle and which requires no cooling fluid pressure generating mechanism, with its attendant added weight, added complication and reduced reliability, and which does not depend upon engine generated pressure to cool the suppressor.In accordance with the present invention, such a suppressor is provided and is made of sheet metal parts, all of which are capable of fabrication and repair by the use of conventional sheet metal fabricating methods and apparatus.In accordance with still a further aspect of the present invention, such a suppressor is provided which defines an annular exhaust gas passage for the engine exhaust gases, which passage increases in cross-sectional area from its forward or upstream end to its after or downstream end so as to constitute a diffuser.It is still a further object of the present invention to provide such an infra-red radiation suppressor which requires minimum cooling fluid flow and which is not prone to flow separation of the cooling fluid film and the adjacent exhaust gas flow from the suppressor parts over which it is flowing.In accordance with a further aspect of the present invention, such an infra-red radiation suppressor is provided and includes an inner body or central plug enveloped within an outer casing such that these parts are supported in spaced relation to define an annular exhaust gas passageway therebetween and such that the selected curvature of the outer surface of the central plug, the inner surface of the outer casing and the midstream path of the annular passageway interact to induce the flow of a cooling air blanket along the outer surface of the central plug and to prevent flow separation of that cooling air blanket and the adjacent exhaust gas flow from the outer surface of the central plug.In accordance with a further aspect of the present invention, an infra-red suppressor is provided which utilizes the ejector principle at at least one station in the suppressor.In accordance with still a further aspect of the present invention, such a suppressor is provided which includes a self-pumping boundary layer control, film cooling slot at substantially the maximum diameter station of the central plug, which slot is defined between wall members in the central plug which cooperate to define a converging passage culminating in the slot, the length of which passage is approximately 10 times the exit height of the slot, thereby cooling the convergent passage defining walls by convection cooling, and so that the cooling air passing through the slot is uniform and positively accelerated to prevent local flow separation of the cooling air from the slot walls upstream of the slot exit and from the central plug wall downstream of the slot exit.
摘要翻译：一种红外辐射抑制器，其适于被定位成改变涡轮轴发动机的排气的流量，并且其尺寸被设计成阻挡视图进入发动机出口，并且包括用于冷却抑制器的可见表面的自泵送喷射器装置。

120. 发明授权

US3981143A Infrared suppressor 失效
标题翻译：红外抑制器
公开(公告)号：US3981143A
公开(公告)日：1976-09-21
申请号：US497786
申请日：1974-08-15
申请人： Thomas D. Ross , Samuel S. Owen
发明人： Thomas D. Ross , Samuel S. Owen
IPC分类号： F02K1/82 , F02K1/26 , F02C7/18
CPC分类号： F02K1/825
摘要： Successful flight of high altitude military aircraft is dependant, in part,pon the ability of the aircraft to remain undetected during flight. However, the hot gas plume is a prime source of infrared radiation, and highly sophisticated infrared sensors have been developed in recent years. A particularly effective infrared radiation suppressor is the plug-type exhaust system. This invention increases heat exchange relationships in the plug-type infrared radiation suppressor without significantly penalizing engine power during suppressor operation.
摘要翻译：高空军用飞机的成功飞行在一定程度上取决于飞机在飞行过程中未被发现的能力。然而，热气羽毛是红外辐射的主要来源，近年来开发出高度复杂的红外传感器。特别有效的红外辐射抑制器是插头式排气系统。本发明增加了插塞式红外辐射抑制器的热交换关系，而在抑制器操作期间不会对发动机功率造成明显损害。

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