知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

207 条记录 (耗时 0.022 秒)

    Combined cycle integrated combustor and nozzle system
    3.
    发明授权
    Combined cycle integrated combustor and nozzle system 有权
    联合循环综合燃烧器和喷嘴系统

    公开(公告)号：US08701379B2

    公开(公告)日：2014-04-22

    申请号：US13008939

    申请日：2011-01-19

    申请人： Melvin J. Bulman

    发明人： Melvin J. Bulman

    IPC分类号： F02C7/00 ,  B64D27/02

    CPC分类号： F02K7/18 ,  F02K7/10 ,  F02K7/14 ,  F02K7/16 ,  F05D2220/10 ,  Y02T50/67

    摘要： An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.

    摘要翻译： 通过节省车辆和发动机开发成本，在Hypersonic联合循环车辆上运行和产生整个所需车辆推力低于Mach4的发动机是有用的。 一个这样的发动机是具有增压器和双模式冲压喷气发动机（DMRJ）的组合循环发动机。 增压器和DMRJ集成在一起，以提供从马赫0到超过马赫数4的有效推力。当助推器将马赫0加速到超过马赫数4，从马赫0到大约马赫数2输入到DMRJ的进入空气 由主要的喷射器推进器加速，其可以从车载氧化剂罐或涡轮压缩机排放空气接收氧化剂。 随着TBCC进一步加速车辆从大约马赫0到来自涡轮的超过马赫数4的排气，并且来自DMRJ的排气被组合在布置在用作空气动力学扼流圈的所述DMRJ的燃烧器部分的下游的公共喷嘴中。

    Relating to air-breathing flight vehicles
    4.
    发明授权
    Relating to air-breathing flight vehicles 有权
    关于呼吸呼吸飞行器

    公开(公告)号：US08662453B2

    公开(公告)日：2014-03-04

    申请号：US12640579

    申请日：2009-12-17

    申请人： Clifford John Richards

    发明人： Clifford John Richards

    IPC分类号： B64D33/02

    CPC分类号： F02C7/042 ,  F02C7/057 ,  F02K1/30 ,  F02K7/10 ,  F02K7/16

    摘要： An air intake for a supersonic air-breathing flight vehicle introduces or injects fluid in order to create predetermined regions of separated flow and an attendant fluid shear layer. This shear layer forms an aerodynamic boundary for the capture flow with a profile determined and optimised by appropriate injection of fluid. The aerodynamic boundary so generated replaces mechanically moveable solid surfaces used to vary the geometry of prior-art intakes. Use of an introduced or injected fluid can provide an advantage of a variable geometry, but with reduced weight and reduced mechanical complexity. In some embodiments, the injection of fluid has the effect of re-energizing any ingested boundary layer, thus obviating the conventional requirement for a bleed system to provide boundary layer control.

    摘要翻译： 用于超音速空气呼吸飞行器的进气口引入或喷射流体以产生分离的流动的预定区域和伴随的流体剪切层。 该剪切层通过适当注入流体确定和优化，形成捕获流的空气动力学边界。 如此产生的空气动力学边界取代了用于改变现有技术摄入的几何形状的机械可移动的固体表面。 使用引入或注入的流体可以提供可变几何形状的优点，但是重量减轻并且机械复杂度降低。 在一些实施例中，流体注入具有重新激发任何摄入的边界层的作用，因此消除了用于提供边界层控制的渗流系统的常规要求。

    Combined Cycle Integrated Combustor and Nozzle System
    5.
    发明申请
    Combined Cycle Integrated Combustor and Nozzle System 有权
    联合循环综合燃烧器和喷嘴系统

    公开(公告)号：US20110107738A1

    公开(公告)日：2011-05-12

    申请号：US13008939

    申请日：2011-01-19

    申请人： Melvin J. Bulman

    发明人： Melvin J. Bulman

    IPC分类号： F02K7/10

    CPC分类号： F02K7/18 ,  F02K7/10 ,  F02K7/14 ,  F02K7/16 ,  F05D2220/10 ,  Y02T50/67

    摘要： An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.

    摘要翻译： 通过节省车辆和发动机开发成本，在Hypersonic联合循环车辆上运行和产生整个所需车辆推力低于Mach4的发动机是有用的。 一个这样的发动机是具有增压器和双模式冲压喷气发动机（DMRJ）的组合循环发动机。 增压器和DMRJ集成在一起，以提供从马赫0到超过马赫数4的有效推力。当助推器将马赫0加速到超过马赫数4，从马赫0到大约马赫数2输入到DMRJ的进入空气 由主要的喷射器推进器加速，其可以从车载氧化剂罐或涡轮压缩机排放空气接收氧化剂。 随着TBCC进一步加速车辆从大约马赫0到来自涡轮的超过马赫数4的排气，并且来自DMRJ的排气被组合在布置在用作空气动力学扼流圈的所述DMRJ的燃烧器部分的下游的公共喷嘴中。

    SCRAMjet arrangement for hypersonic aircraft
    6.
    发明授权
    SCRAMjet arrangement for hypersonic aircraft 有权
    用于超音速飞机的SCRAM喷射装置

    公开(公告)号：US07828243B2

    公开(公告)日：2010-11-09

    申请号：US11196187

    申请日：2005-08-03

    申请人： Allen A. Arata

    发明人： Allen A. Arata

    IPC分类号： F02K7/10 ,  F02K7/16 ,  B64D27/16

    CPC分类号： F02K7/14 ,  F02C6/00 ,  F02K7/16 ,  F05D2220/80

    摘要： Hypersonic aircraft having a lateral arrangement of turbojet and SCRAMjet engines are disclosed. The SCRAMjet engines may be positioned laterally outboard of the turbojet engines. In one embodiment, the turbojet inlet and outlet openings may be covered during use of the SCRAMjets in order to provide compression and expansion ramps for the laterally adjacent SCRAMjet engines. The side-by-side arrangement of the turbojet and SCRAMjet engines reduces the vertical thickness of the aircraft, thereby reducing drag and potentially increasing performance.

    摘要翻译： 公开了具有涡轮喷气发动机和SCRAM喷射发动机的横向布置的超音速飞机。 SCRAMjet发动机可以横向位于涡轮喷气发动机外侧。 在一个实施例中，涡轮喷气发动机入口和出口开口可以在SCRAM喷射器的使用期间被覆盖，以便为侧向相邻的SCRAM喷射发动机提供压缩和膨胀斜坡。 涡轮喷气发动机和SCRAM喷气发动机的并排布置降低了飞机的垂直厚度，从而减少了阻力并且潜在地提高了性能。

    Centerline compression turbine engine
    7.
    发明申请
    Centerline compression turbine engine 审中-公开
    中心线压缩涡轮发动机

    公开(公告)号：US20090067983A1

    公开(公告)日：2009-03-12

    申请号：US11900010

    申请日：2007-09-10

    申请人： William R. Estlick

    发明人： William R. Estlick

    IPC分类号： F02K3/00 ,  F04D25/16 ,  F04D19/02

    CPC分类号： F01D5/03 ,  F02K7/005 ,  F02K7/16 ,  F04D13/0646 ,  F04D19/024 ,  F04D19/026 ,  F04D25/04 ,  F04D29/058 ,  F05D2220/10 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2300/133 ,  F05D2300/21 ,  F05D2300/507 ,  F05D2300/603 ,  Y02T50/672

    摘要： A Centerline Compression Turbofan Engine reconfigures the current technology eliminating the shaft and placing the combustor at the intake of the engineTurbine blades mounted on the inside of consecutive rings are curved and angled so that they compress air towards the centerline and backward along the axis of the engine as they rotate. High speed exhaust gasses from the combustor coming into contact with the turbine blades provide the rotational drive for each turbine blade array.Exhaust gasses from the combustion chamber and air from the intake are compressed through consecutively smaller turbine blade arrays along the entire length of the engine until it exits the variable exhaust nozzle.Said configuration produces a jet of a high speed exhaust gas for propulsive purposes.

    摘要翻译： 中心线压缩涡轮发动机重新配置当前技术，消除轴并将燃烧器放置在发动机的入口处。安装在连续环的内侧的涡轮叶片弯曲和成角度，使得它们沿着中心线压缩空气并沿着 发动机旋转。 来自与涡轮机叶片接触的燃烧器的高速排放气体为每个涡轮机叶片阵列提供旋转驱动。 来自燃烧室的排气和来自进气口的空气沿着发动机整个长度的连续更小的涡轮叶片阵列被压缩，直到其离开可变排气喷嘴。 所述构造产生用于推进目的的高速废气喷射。

    Rotary ramjet turbo-generator
    8.
    发明申请
    Rotary ramjet turbo-generator 有权
    旋转式冲压发动机

    公开(公告)号：US20070056290A1

    公开(公告)日：2007-03-15

    申请号：US11326068

    申请日：2006-01-05

    申请人： Werner Dahm

    发明人： Werner Dahm

    IPC分类号： F02K7/10

    CPC分类号： F02K7/16 ,  F05D2250/82 ,  Y02T50/671

    摘要： A Brayton-cycle rotary ramjet engine (10) operated within the confines of a helically elongated pass-through duct formed between a preferably stationary radially outward surface (14) and an outer rotating flow channel (36). The flow channel (36) is contoured between its inlet (34) and outlet (38) to include a supersonic diffuser (40), a combustor (42) and an expansion nozzle (44). Gaseous fuel, or liquid fuel atomized by a fuel slinger (58) within a housing (46), or solid fuel in the form of fine particulates, is inter-mixed with an oxidizer prior to being directed to the flow channel inlets (34). The air and fuel are combusted in the flow channels (36) and exhausted through the rear of the housing (46). A generator (22) can be coupled to a power shaft (18) to convert net shaft power into electricity. Preferably, the rotor (24) and stator (12) are fabricated from a ceramic or other high-temperature material so that combustor exit temperatures (T3) can be operated at highly efficient levels.

    摘要翻译： 布雷顿循环旋转冲压喷气发动机（10）在形成在优选固定的径向向外表面（14）和外部旋转流动通道（36）之间的螺旋形细长通道管道的范围内操作。 流道（36）在其入口（34）和出口（38）之间形成轮廓，以包括超音速扩散器（40），燃烧器（42）和膨胀喷嘴（44）。 通过壳体（46）内的燃料抛油环（58）或微细颗粒形式的固体燃料雾化的气体燃料或液体燃料在被引导至流动通道入口（34）之前与氧化剂相互混合， 。 空气和燃料在流动通道（36）中燃烧并且通过壳体（46）的后部排出。 发电机（22）可联接到动力轴（18），以将净轴功率转换成电力。 优选地，转子（24）和定子（12）由陶瓷或其它高温材料制成，使得燃烧器出口温度（T 3 3 3）可以以高效率的水平运行。

    Methods and apparatus for assembling a gas turbine engine
    9.
    发明申请
    Methods and apparatus for assembling a gas turbine engine 有权
    用于组装燃气涡轮发动机的方法和装置

    公开(公告)号：US20060064961A1

    公开(公告)日：2006-03-30

    申请号：US10955614

    申请日：2004-09-30

    申请人： James Johnson

    发明人： James Johnson

    IPC分类号： F02K3/02

    CPC分类号： F02K3/077 ,  F02C7/042 ,  F02K3/075 ,  F02K7/16

    摘要： A method for assembling a gas turbine engine includes providing a core engine, and providing a flade system including a flade stream augmentor positioned within a flade duct. The method also includes channeling airflow through the core engine to produce engine thrust, channeling airflow through the flade duct to produce engine thrust, and igniting a portion of the airflow channeled through the flade duct using the flade stream augmentor to increase the amount of thrust produced by the flade system.

    摘要翻译： 一种用于组装燃气涡轮发动机的方法包括提供一种核心发动机，并提供一种包括定位在飞边管道内的落叶加油器的落叶系统。 该方法还包括引导通过核心发动机的气流以产生发动机推力，将气流引导通过飞行器管道以产生发动机推力，并且使用落叶流增压器点燃引导通过飞行器管道的气流的一部分，以增加产生的推力量 由淡菜系统。