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公开(公告)号：US5794851A
公开(公告)日：1998-08-18
申请号：US570172
申请日：1995-12-07
申请人： William Kevin Barcza
发明人： William Kevin Barcza
CPC分类号： F02K1/805
摘要： A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and apparatus for sealing between the external fairing and the divergent section. The convergent section communicates with the augmentor on one end and with the divergent section on the opposite end. The end of the divergent section opposite that attached to the convergent section is pivotly attached to the external fairing. The divergent section includes a plurality of divergent flaps and divergent flap seals circumferentially spaced. The apparatus for sealing between the external fairing and the divergent section attaches to the divergent flaps and divergent flap seals and mates with the external fairing.
摘要翻译： 提供一种用于燃气涡轮发动机的喷嘴，其包括外壳，收敛部分，发散部分，外部整流罩和用于在外部整流罩和发散部分之间进行密封的装置。 收敛部分在一端与增压器通信，并在相对端与发散部分通信。 与会聚部分相对的发散部分的端部枢转地附接到外部整流罩。 发散部分包括沿圆周间隔开的多个发散的翼片和发散的翼片密封件。 外部整流罩和发散部分之间的密封装置连接到发散的翼片和发散的翼片密封件并与外部整流罩配合。
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公开(公告)号：US5771681A
公开(公告)日：1998-06-30
申请号：US710425
申请日：1996-09-17
申请人： Peter K. C. Rudolph
发明人： Peter K. C. Rudolph
摘要： A fluid mixing apparatus for mixing primary exhaust and secondary airflow in a turbofan engine with provision for changing the ratio of secondary airflow to primary exhaust cross-sectional areas in the mixing plane. The mixing apparatus includes a segmented annulus (50) attached to the aft end of an engine generator casing (24), the annulus having a plurality of segments of which at least a portion are movable segments (52) hingedly connected to the generator. Each movable segment has an inboard position (54) in which the cross-sectional area ratio is increased and an outboard position (56) in which the ratio is decreased. A number of mixing devices (62) are connected to the segments. A repositioning assembly (96) moves the movable segments between their inboard and outboard positions. A first preferred embodiment of the mixing apparatus includes a number of stationary segments (60) interspersed between the movable segments (52). The mixing devices (62) are attached to the stationary segments (60). A second preferred embodiment of the mixing apparatus includes only movable segments (52), with the mixing devices (62) being attached to the movable segments. Expansion mechanisms (96) are provided between adjacent movable segments, as needed.
摘要翻译： 一种流体混合装置，用于混合涡轮风扇发动机中的一次排气和二次气流，其设置用于改变混合平面中二次气流与一次排气横截面积的比率。 混合装置包括附接到发动机发电机壳体（24）的后端的分段环（50），所述环具有多个段，其中至少一部分是铰接地连接到发电机的可动段（52）。 每个可移动段具有其中横截面积比增加的内侧位置（54）和该比率减小的外侧位置（56）。 多个混合装置（62）连接到该段。 重新定位组件（96）使可动部分在其内侧和外侧位置之间移动。 混合装置的第一优选实施例包括散布在可动部分（52）之间的多个固定部分（60）。 混合装置（62）附接到固定段（60）。 混合装置的第二优选实施例仅包括可移动部分（52），混合装置（62）附接到可动部分。 根据需要，在相邻的可移动部分之间设置扩展机构（96）。
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公开(公告)号：US5755092A
公开(公告)日：1998-05-26
申请号：US732926
申请日：1996-10-17
摘要： An exhaust nozzle mixer for a turbojet engine is disclosed having a multi-lobed shroud extending from the exhaust nozzle of the turbojet engine, the shroud having a plurality of radially oriented lobes forming a plurality of gas mixing channels, each having a first cross-section in a plane extending substantially perpendicular to the longitudinal axis of the engine, as well as a flared lobe having a greater circumferential width than the remainder of the lobes to accommodate the engine mounting pylon. A baffle member extends radially inwardly from the mounting pylon toward the longitudinal axis of the engine such that the baffle extends into the flared lobe to form a plurality of cross-sections, each of such cross-sections being generally equal to each of remainder of the cross-sections of the multi-lobed shroud.
摘要翻译： 公开了一种用于涡轮喷气发动机的排气喷嘴混合器，其具有从涡轮喷气发动机的排气喷嘴延伸的多叶形护罩，护罩具有多个径向定向的凸角，形成多个气体混合通道，每个气体混合通道具有第一横截面 在基本上垂直于发动机的纵向轴线延伸的平面中，以及具有比其余的叶片更大的周向宽度以扩张发动机安装塔的扩口凸角。 挡板构件从安装支架向发动机的纵向轴线径向向内延伸，使得挡板延伸到扩张的凸角中以形成多个横截面，每个这样的横截面通常等于 横断面的多叶形护罩。
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公开(公告)号：US5706651A
公开(公告)日：1998-01-13
申请号：US521139
申请日：1995-08-29
CPC分类号： F02K3/06 , B64D33/06 , F02C7/045 , F02C7/24 , F02K1/386 , F02K1/48 , F02K1/60 , F05D2220/327 , Y02T50/672
摘要： A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser includes opposing doors rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly. A bleed air valve, selectively operational to bleed air from the core engine when the valve is open, is ducted for directing bleed air to the vicinity of the common nozzle.
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公开(公告)号：US5666802A
公开(公告)日：1997-09-16
申请号：US501116
申请日：1995-09-08
申请人： Jean-Pierre Lair
发明人： Jean-Pierre Lair
CPC分类号： F02K1/06 , F02K1/11 , F02K1/386 , F02K1/60 , Y02T50/672
摘要： A thrust reverser system for a turbine engine of the type having a central relatively hot gas generator nozzle conducting a core flow and a relatively cold duct conducting a fan flow and surrounding the hot flow, a pair of thrust reverser door, each of the doors being pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of the engine so as to pivot between a stowed position in which the doors are out of the direct path of exhaust from the engine and a deployed position in which the doors are in the path of the engine exhaust for deflecting the exhaust and creating a braking thrust, a flow modifying arrangement acting on the hot gas generator nozzle for simultaneously decreasing the total pressure of the core flow and increasing the total pressure of the fan flow by increasing the area of the hot gas generator nozzle at the discharge end thereof and moving the boundary between the hot gas and cold gas flows radially outwardly.
摘要翻译： PCT No.PCT / US94 / 01575 Sec。 371日期1995年9月8日 102（e）1995年9月8日PCT PCT 1994年2月8日PCT公布。 第WO94 / 18446号公报 日期1994年8月18日一种用于涡轮发动机的推力反向器系统，其具有导向芯流的中心相对较热的气体发生器喷嘴和导致风扇流并围绕热流的相对冷的管道，一对推力反向器门， 每个门枢转地安装在相对于发动机的排气喷嘴基本上直径定位的轴线上，以便在收起的位置之间枢转，在该收起位置之间的门从发动机的直接排出路径排出， 门处于发动机排气路径中以使排气偏转并产生制动推力的位置，作用在热气体发生器喷嘴上的流动改变装置，用于同时降低核心流量的总压力并增加总压力 通过增加热气体发生器喷嘴在其排出端处的面积并使热气体与冷气体流动之间的边界流动 向外。
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公开(公告)号：US5518311A
公开(公告)日：1996-05-21
申请号：US225397
申请日：1994-04-08
申请人： Rolf Althaus , Alexander Beeck , Yau-Pin Chyou , Adnan Eroglu
发明人： Rolf Althaus , Alexander Beeck , Yau-Pin Chyou , Adnan Eroglu
IPC分类号： F23R3/12 , B01F5/00 , B01F5/04 , B01F5/06 , F02K1/38 , F23D14/62 , F23D14/70 , F23R3/16 , F23R3/28 , F23R3/32 , F23R3/34 , B01F15/02
CPC分类号： B01F5/061 , B01F5/0451 , B01F5/0473 , B01F5/0656 , F02K1/386 , F23R3/16 , F23R3/286
摘要： A mixing chamber for introducing a gaseous secondary flow into a gaseous, ducted main flow includes a plurality of vortex generators to facilitate mixing of the flows. The secondary main flow has a substantially smaller mass flow than the main flow. The main flow is guided via the plurality of vortex generators arranged adjacent to one another over the width or the periphery of the duct through which flow takes place. The height (h) of the vortex generators is at least 50% of the height (H) of the duct through which flow takes place. The secondary flow is fed into the duct in the immediate region of tile vortex generators. The mixing chamber according to the invention exhibits extraordinarily short mixing distances in the mixing chamber with a simultaneously low pressure loss.
摘要翻译： 用于将气态二次流引入气体管道主流的混合室包括多个涡流发生器以便于流动的混合。 次要主流体的质量流量大于主流量。 主流通过多个涡流发生器引导，多个涡流发生器彼此相邻布置在通过其流动的管道的宽度或周边上。 涡流发生器的高度（h）至少为发生管道的高度（H）的50％。 二次流在瓦片涡流发生器的直接区域内进入管道。 根据本发明的混合室在混合室中表现出非常短的混合距离，同时具有低的压力损失。
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公开(公告)号：US5117628A
公开(公告)日：1992-06-02
申请号：US469982
申请日：1990-01-25
申请人： John M. Koshoffer
发明人： John M. Koshoffer
CPC分类号： F02K1/48 , F02K1/386 , F02K3/10 , F02K3/105 , F05D2260/20 , Y02T50/675
摘要： A mixer arrangement for a bypass type gas turbine engine is disclosed. The mixer is convoluted and generally annular and defines radially and axially extending first and second chutes adapted to receive, respectively, a hot gas stream from the engine core and a cooler gas stream from the fan duct. A pre-mixer is disposed upstream of the mixer and is also convoluted and is aligned in flow communication with the second chutes of the mixer such that the hot gas stream received by the pre-mixer is mixed with the cooler fan air stream received by the second chutes to raise the temperature of the fan air entering an afterburner section of the engine.
摘要翻译： 公开了一种用于旁路式燃气涡轮发动机的混合器装置。 混合器是回旋的并且大致环形并且限定径向和轴向延伸的第一和第二滑槽，其适于分别接收来自发动机芯的热气流和来自风扇导管的较冷气体流。 预混合器设置在混合器的上游并且还被卷积并且与混合器的第二滑槽流动连通地对准，使得由预混合器接收的热气流与由所述混合器接收的冷却器风机气流混合 第二滑槽，以提高进入发动机加燃器部分的风扇空气的温度。
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58.发明授权
公开(公告)号：US4984732A
公开(公告)日：1991-01-15
申请号：US305565
申请日：1989-02-03
IPC分类号： B21D26/055 , F02K1/38
CPC分类号： B21D26/055 , F02K1/386 , Y10S72/709 , Y10T29/49229 , Y10T29/49805
摘要： A method is provided for achieving predetermined thickness requirements throughout a superplastically formed structure having extreme contours. A laminate assembly of sheets of a metal capable of exhibiting superplasticity, such as titanium alloy, is formed by a combination of superplastic forming and diffusion bonding. The shapes and positioning of the sheets is selected to provide extra metal where the greatest degree of stretching is necessary, such as around the lobes of an exhaust mixer for a turbofan aircraft engine. The gauge can thus be controlled throughout the structure while avoiding weak points and undue weight.
摘要翻译： 提供了一种用于在具有极端轮廓的超塑性形成结构中实现预定厚度要求的方法。 通过超塑性成形和扩散接合的组合形成能够显示超塑性的金属片的层压组件，例如钛合金。 选择片材的形状和定位以提供额外的金属，其中需要最大程度的拉伸，例如用于涡轮风扇飞机发动机的排气混合器的叶片周围。 因此，可以在整个结构中控制量规，同时避免弱点和不适当的重量。
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公开(公告)号：US4791783A
公开(公告)日：1988-12-20
申请号：US325156
申请日：1981-11-27
申请人： Robert E. Neitzel
发明人： Robert E. Neitzel
CPC分类号： F02C6/08 , F01D17/162 , F02K3/075
摘要： A convertible aircraft engine, capable of turboshaft and/or turbofan modes of operation, is provided in a configuration that combines certain components to permit variation in bypass flow to match engine airflows with the mode of engine operation. The provided components permit the engine to decrease the power requirements of the engine's forward fan when the engine is operated in the turboshaft mode. To permit a decrease in fan power requirements, the fan is split into an outer portion and an inner portion separated by a rotating shroud. Airflow into the fan's outer portion is controlled with a part span inlet guide vane and an outlet guide vane. The guide vanes can be used to lessen the load on the outer portion of the fan while the inner portion continues to accelerate and compress a normal airflow into an engine compressor for supplying the engine's core. The power normally used to drive the fan outer portion is used instead to power a transfer shaft in the turboshaft mode.
摘要翻译： 提供了能够具有涡轮轴和/或涡轮风扇运行模式的敞篷式飞机发动机，其结合了某些部件以允许旁路流量的变化以使发动机气流与发动机运转的模式相匹配。 当发动机在涡轮轴模式下操作时，所提供的部件允许发动机降低发动机的前风扇的功率要求。 为了减少风扇功率的要求，风扇被分割成由旋转罩隔开的外部部分和内部部分。 进入风扇外部的气流由部分跨度入口导向叶片和出口导向叶片控制。 导向叶片可以用于减小风扇外部的负载，同时内部部分继续加速并将正常的气流压缩到用于供应发动机芯的发动机压缩机中。 通常用于驱动风扇外部部分的电力代替在涡轮轴模式下为传递轴供电。
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60.发明授权Plume diluter diverter assembly for a turbine engine of a heavier than air machine 失效用于比空气机重的涡轮发动机的吹气稀释器转向器组件
公开(公告)号：US4662174A
公开(公告)日：1987-05-05
申请号：US740783
申请日：1985-06-03
申请人： Francois V. Toulmay
发明人： Francois V. Toulmay
CPC分类号： B64D33/04 , B64D2033/045
摘要： The assembly comprises a collector nozzle which is fixed to a turbine engine and which is elbowed laterally towards the exterior and which debouches into injection nozzles which are also elbowed and which open into a mixer masked laterally by means of a fairing, of which a shaped forward section defines, with an internal shaped screen and a central plug, a semi dynamic principal air inlet. The aspirated air dilutes the gas in the mixer which is terminated by means of an elbow directed upwardly and which can pivot about a transverse axis. In the position of maximum deviation upwardly this elbow masks the hot parts of the assembly from the rear. The assembly is particularly useful for equipping helicopters with lateral exhaust gas turbine engines, and it can be original equipment or retrofitted. The assembly serves to reduce the infra red emission from the helicopter, to defeat infra red homing missiles.
摘要翻译： 组件包括收集器喷嘴，其固定到涡轮发动机并且朝向外部侧向弯曲并且其被分解成注入喷嘴，喷嘴也是弯头的，并且通过整流罩侧向打开的混合器敞开， 部分定义了内部形状的屏幕和中央插头，半动态主要空气入口。 抽吸的空气稀释在混合器中的气体，其通过向上指向的弯头终止，并且其可以围绕横向轴线枢转。 在最大偏差向上的位置，该肘部从后部遮盖组件的热部件。 该组件特别适用于为直升机配备侧向排气涡轮发动机，并且它可以是原始设备或改装。 该装置用于减少直升机的红外辐射，以击败红外导弹。
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