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公开(公告)号：US4966526A
公开(公告)日：1990-10-30
申请号：US379305
申请日：1989-07-13
IPC分类号： B64C27/46 , B64C27/32 , B64C27/467
CPC分类号： B64C27/325
摘要： A circulation control rotor system for aircraft in which compressed air is directly supplied at generally constant pressure to plenums in the rotor blades and discharged through area controlled slots, the area controlling means involving camming surfaces and being actuated by cyclic, collective, aircraft vibration and flight stability inputs.
摘要翻译： 一种用于航空器的循环控制转子系统，其中压缩空气以一般恒定的压力直接供应到转子叶片中的通风室并通过区域控制的槽排出，该区域控制装置涉及凸轮表面并由循环，集体，飞机振动和飞行 稳定性输入。
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公开(公告)号：US6134879A
公开(公告)日：2000-10-24
申请号：US454167
申请日：1989-12-21
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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公开(公告)号：US5165232A
公开(公告)日：1992-11-24
申请号：US812091
申请日：1991-12-23
CPC分类号： F02C7/27 , B64D41/00 , F05D2220/50 , Y02T50/44 , Y02T50/671
摘要： There is provided by the present invention an accumulator system for turb engine start-ups that has comparable weight and bulk to a conventional auxiliary power unit system but which has instantaneous second start capability.
摘要翻译： 本发明提供了一种用于涡轮发动机起动器的蓄能器系统，其具有与常规辅助动力单元系统相当的重量和体积，但具有瞬时第二启动能力。
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公开(公告)号：US4304094A
公开(公告)日：1981-12-08
申请号：US95135
申请日：1979-11-16
申请人： Armand F. Amelio
发明人： Armand F. Amelio
CPC分类号： F02C7/052
摘要： An engine air particle separator for use with a turbine engine and providing a first engine air flow path to the engine inlet in which foreign particles are separated from the air entering engine, and a second direct flow path for air to the engine inlet presenting minimum pressure drop and such that the ram air flows directly into the engine inlet. The second flow path includes actuatable blow-in doors which are actuated by a pneumatic door actuator mechanism operable to cause the doors to close upon the admission of air at operating pressure to the mechanism. Mechanism is provided to prevent the doors from opening when actuating air pressure is applied to the door actuator mechanism but falls below a preselected limit and to permit the doors to open in response to spring bias and ram pressure acting thereagainst when the air at actuating pressure is withdrawn.
摘要翻译： 一种发动机空气颗粒分离器，用于与涡轮发动机一起使用，并且向发动机入口提供第一发动机空气流动路径，其中外来颗粒与进入发动机的空气分离，以及用于空气到发动机入口的第二直接流动路径，其具有最小压力 使得冲压空气直接流入发动机入口。 第二流路包括可致动的吹入门，其由气动门致动器机构致动，该气动门致动器机构可操作以在入口处的空气在机构的操作压力下使门关闭。 提供机构以防止当致动空气压力施加到门致动器机构但是低于预定极限时允许门打开，并且允许门响应于当致动压力下的空气为起动时的弹簧偏压和压头作用而打开门 取消。
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公开(公告)号：US5697394A
公开(公告)日：1997-12-16
申请号：US20015
申请日：1993-03-02
申请人： David R. Smith , Armand F. Amelio
发明人： David R. Smith , Armand F. Amelio
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/022 , B64D2033/0246 , Y10T137/0536 , Y10T137/0645
摘要： A turbine engine inlet system includes a duct 14 to deliver air to the engine, inlet lips 16 and 52 to smooth the entry of air flowing into the duct, a screen 50 between the lips 52 and 16 for passage of inlet air, 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 positionable in a retracted position during normal flight, is extendable outward to a second position substantially flush with the screen 50 for maximum protection against foreign object damage (FOD), and is further extendable outward to a third position beyond the screen to provide an air bypass path when the screen is iced-over.
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管道14，入口唇缘16和52，以平滑流入管道的空气的进入，用于通过入口空气的嘴唇52和16之间的筛网50， 部分18淹没在飞行器皮肤轮廓内，以向管道提供一定程度的柱塞恢复，并且可在正常飞行期间定位在缩回位置的可移动导风板20可向外延伸到基本上与屏幕50齐平的第二位置 最大限度地防止异物损坏（FOD），并且可以进一步向外延伸到超出屏幕的第三位置，以在屏幕结冰时提供空气旁路。
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公开(公告)号：US5694763A
公开(公告)日：1997-12-09
申请号：US507686
申请日：1990-04-11
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。
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公开(公告)号：US4238971A
公开(公告)日：1980-12-16
申请号：US970763
申请日：1978-12-18
申请人： Armand F. Amelio
发明人： Armand F. Amelio
CPC分类号： B63H21/213 , F16C1/10 , F16C1/26 , F16C11/0614 , F02B61/045 , Y10T403/11 , Y10T74/20012 , Y10T74/2045
摘要： A releasable push-pull sheathed cable control system in which the sheathed cable extends between the control input and the control output and includes a looped portion fixed at one end and releasably fixed at its other end so that tension or compression loading of the cable following cable jamming anywhere within the sheath or therebeyond in a control system will cause deformation or the looped portion and release of one end of the sheathed cable.
摘要翻译： 一种可释放的推挽式护套电缆控制系统，其中护套电缆在控制输入端和控制输出端之间延伸，并包括固定在一端的环形部分，并可释放地固定在其另一端，使电缆跟随电缆的张力或压缩载荷 在控制系统中的护套或其内的任何地方卡住将导致护套电缆的一端的变形或环形部分和释放。
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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
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。
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公开(公告)号：US5779288A
公开(公告)日：1998-07-14
申请号：US118066
申请日：1993-09-08
申请人： Armand F. Amelio
发明人： Armand F. Amelio
CPC分类号： E05C5/04 , B64D29/06 , Y10T292/1099 , Y10T292/218
摘要： A low profile latch mechanism for an access panel that minimizes external structural discontinuities while concomitantly providing external access to engage and/or disengage the latch mechanism for closing and/or opening of the access panel. The latch mechanism includes an insert member mounted in rotatable combination with the internal surface of the access panel, a captured floating nut mounted in nonrotatable combination with the internal surface of a frame segment, a safety lock member mounted for axial displacement within the captured floating nut, and a removable key member. The removable key member is insertable through an access aperture in the access panel to engage the insert member for rotation thereof to threadingly engage the captured floating nut to close the access panel. The safety lock member is biased to engage the insert member to lock the low profile latch mechanism in the fully engaged state upon removal of the key member. The removable key member is inserted through the access aperture to mechanically disengage the safety lock member from the insert member to initiate the disengagement procedure. Counter-rotation of the key member causes the insert member to threadingly disengage from the capture floating nut, which causes the access panel to be biased to a partially open position wherein the access panel may be fully opened manually.
摘要翻译： 一种用于进入面板的薄型闩锁机构，其最小化外部结构不连续性，同时伴随地提供外部接近以接合和/或解除用于闭合和/或打开检修面板的闩锁机构。 所述闩锁机构包括与所述检修面板的内表面可旋转地组合安装的插入件，与框架部分的内表面安装成不可旋转组合的捕获浮动螺母，安装在所捕获的浮动螺母内的轴向位移的安全锁定构件 ，以及可拆卸的键构件。 可拆卸的键构件可通过检修面板中的进入孔插入，以接合插入构件以使其旋转，以与被捕获的浮动螺母螺纹接合以闭合检修面板。 安全锁定构件被偏置以接合插入构件，以在移除键构件时将低轮廓闩锁机构锁定在完全接合状态。 可拆卸的键构件通过进入孔插入以使安全锁定构件与插入构件机械地脱离以启动脱离过程。 键构件的反向旋转使得插入构件与捕获浮动螺母螺纹脱离，这使得检修面板被偏压到部分打开位置，其中检修面板可以手动完全打开。
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公开(公告)号：US5699965A
公开(公告)日：1997-12-23
申请号：US374025
申请日：1989-06-30
申请人： Armand F. Amelio
发明人： Armand F. Amelio
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , Y02T50/671
摘要： An IR suppressor produces a thin "ribbon" exhaust plume using a tapered exhaust manifold which has a plurality of discrete exhaust nozzles that are longitudinally aligned with the exhaust manifold. Optionally, the nozzles extend within but are spaced apart from mixing ducts which are open to the ambient air at both ends. The mixing ducts mix ambient air with the exhaust plume. In another aspect of this invention, a single nozzle (which is longitudinally aligned with the manifold) is substituted for the plurality of discrete exhaust nozzles. In this aspect, the nozzle extends within but is spaced apart from a mixing duct which is open at both ends and has a curve sufficient to block a line of sight to the nozzle. A helicopter that has a rotatable IR suppressor so that the exhaust can be directed substantially parallel to the helicopter blades when the blades are not turning to protect them from exhaust heat is also disclosed.
摘要翻译： IR抑制器使用具有与排气歧管纵向对准的多个离散排气喷嘴的锥形排气歧管产生薄的“带状”排气羽流。 可选地，喷嘴在内部延伸，但是与在两端的环境空气开放的混合管道间隔开。 混合管道将环境空气与排气羽流混合。 在本发明的另一方面，单个喷嘴（其与歧管纵向对齐）被代替多个离散的排气喷嘴。 在这方面，喷嘴在其两端敞开的混合管道内延伸而间隔开，并具有足以阻挡喷嘴的视线的曲线。 一种具有可旋转的IR抑制器的直升机，其特征在于还公开了当叶片不转动以保护它们免于排热时，排气可以直接指向直升机叶片。
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