利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

77 条记录 (耗时 0.02 秒)

    Airflow modulation for dual mode combined cycle propulsion systems
    41.
    发明授权
    Airflow modulation for dual mode combined cycle propulsion systems 有权
    双模式联合循环推进系统的气流调节

    公开(公告)号：US08429893B2

    公开(公告)日：2013-04-30

    申请号：US12539451

    申请日：2009-08-11

    申请人： George D Rupp ,  Trajaen J. Troia

    发明人： George D Rupp ,  Trajaen J. Troia

    IPC分类号： F02K7/02 ,  F02K7/16

    CPC分类号： F01D17/12 ,  F01D5/02 ,  F01D9/04 ,  F02C7/042 ,  F02K3/02 ,  F02K7/075 ,  F02K7/16 ,  F02K7/20 ,  F05D2220/10 ,  F05D2300/502 ,  Y02T50/672

    摘要： The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.

    摘要翻译： 本发明涉及一种机械系统和方法，其调节与整合中等涡轮发动机和诸如恒定体积燃烧室（CVC）排列的高马赫发动机的飞机发动机结合使用的飞行器入口扩散器中的气流，或 冲压喷气式排气装置，与涡轮机共同形成进气口。 调制系统使用两个铰接部件，一个可移动的空气流动管道和一个铰接锥体。 处于第一位置的空气流动管道处于与来自涡轮机的圆形进气面的第一位置专用气流连通，以从进气扩散器接收空气。 在该配置中，可膨胀锥体处于缩回位置，并且不会使气流重定向，并允许飞行器以低速模式操作，因为只有涡轮喷气机接收气流。 在过渡速度模式中，空气流动管道缩回以允许空气流动到涡轮喷气机和CVC。 铰链锥体完全覆盖涡轮喷气圆形进气面，将空气仅引导到高马赫飞机发动机，以使飞机能够以高速运行。

    Linear acoustic pulsejet
    43.
    发明授权
    Linear acoustic pulsejet 有权
    线性脉冲喷射

    公开(公告)号：US07427048B2

    公开(公告)日：2008-09-23

    申请号：US11190264

    申请日：2005-07-27

    申请人： Richard P Ouellette

    发明人： Richard P Ouellette

    IPC分类号： B64B1/36

    CPC分类号： F02K7/075 ,  F02K7/02

    摘要： A linear acoustic pulsejet (LAP) including a body having a first side panel and an opposing substantially parallel second side panel. A plurality of substantially parallel intercostals are orthogonally connected to each of the first and second side panels to create a plurality of pulsejet cells within an interior of the body. The LAP additionally includes a linear inlet cap over a top of the body that forms an air flow pathway (AFP) between the linear inlet cap and an exterior of an inlet section of the body. The linear inlet cap forms the AFP to have a substantially 180° turn between an exterior of the body and an interior of the pulsejet cells.

    摘要翻译： 一种线性声脉冲喷射（LAP），包括具有第一侧板和相对的基本平行的第二侧板的主体。 多个基本上平行的肋间与第一和第二侧板中的每一个正交连接以在主体的内部产生多个脉冲喷射单元。 LAP还包括在主体的顶部上的线性入口盖，其在线性入口盖和主体的入口部分的外部之间形成空气流动路径（AFP）。 线性入口盖形成AFP以在主体的外部和脉冲喷射单元的内部之间具有大致180°的转弯。

    Pulsed combustion fluidic nozzle
    44.
    发明申请
    Pulsed combustion fluidic nozzle 审中-公开
    脉冲燃烧流体喷嘴

    公开(公告)号：US20070144141A1

    公开(公告)日：2007-06-28

    申请号：US11317222

    申请日：2005-12-22

    申请人： Gary Roberge ,  James Wozniak ,  Wendell Twelves

    发明人： Gary Roberge ,  James Wozniak ,  Wendell Twelves

    IPC分类号： F02K3/02

    CPC分类号： F02K1/30 ,  F02K7/075 ,  F05D2240/126 ,  Y02T50/671

    摘要： A propulsion system for producing thrust includes a turbine engine. The engine has a compressor, a combustor downstream of the compressor along a flow path, and a turbine downstream of the combustor along the flow path. A plurality of combustion conduits have outlets positioned to discharge combustion gas to form a fluidic nozzle throat.

    摘要翻译： 用于产生推力的推进系统包括涡轮发动机。 发动机具有压缩机，沿着流路在压缩机下游的燃烧器和沿着流动路径的燃烧器下游的涡轮机。 多个燃烧管道具有用于排出燃烧气体以形成流体喷嘴喉部的出口。

    Vertical takeoff and landing aircraft
    47.
    发明授权
    Vertical takeoff and landing aircraft 有权
    垂直起降飞机

    公开(公告)号：US06976654B2

    公开(公告)日：2005-12-20

    申请号：US10829743

    申请日：2004-04-22

    申请人： Richard P. Ouellette ,  Aaron J. Kutzmann

    发明人： Richard P. Ouellette ,  Aaron J. Kutzmann

    IPC分类号： B64C1/14 ,  B64C29/00 ,  B64D5/00 ,  B64D27/02 ,  B64D27/20 ,  F02K7/075

    CPC分类号： F02K7/075 ,  B64C1/1415 ,  B64C29/0058 ,  B64D5/00 ,  B64D27/023 ,  B64D27/20 ,  Y02T50/44 ,  Y02T50/672

    摘要： A flight capable mobile platform adapted for covert deployment is provided. The mobile platform is additionally adapted to have a reduced vulnerability to hostile detection and aggression. The mobile platform includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The mobile platform additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constructed such that the mobile platform can be transported by a larger second mobile platform. This allows for the mobile platform to be aerial deployed from the larger second mobile platform. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the mobile platform is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.

    摘要翻译： 提供了一种适合隐蔽部署的具有行动能力的移动平台。 移动平台还适应于对敌对检测和侵略的脆弱性降低。 移动平台包括具有一对侧壁和底部的机身。 侧壁和底部形成一个装甲有效载荷舱。 移动平台还包括连接到机身的一对翼。 机翼具有固定的翼展，其构造使得移动平台能够被较大的第二移动平台运输。 这允许移动平台从较大的第二移动平台进行空中部署。 每个侧壁包括向外倾斜的至少一个脉冲喷射器推力增强器（PETA）组。 因此，每个PETA银行产生的推力排气被引导向下并远离有效载荷舱的中心线。 此外，移动平台的底部适于允许货物的进出口。 军事部队，从有效载荷湾。

    Engine systems and methods
    48.
    发明申请
    Engine systems and methods 审中-公开
    发动机系统和方法

    公开(公告)号：US20050235957A1

    公开(公告)日：2005-10-27

    申请号：US11016702

    申请日：2004-12-16

    申请人： Ronnie Duncan

    发明人： Ronnie Duncan

    IPC分类号： F02B51/06 ,  F02K7/02 ,  F02K7/075 ,  F02K9/00

    CPC分类号： F02K7/02 ,  F02B51/06 ,  F02K7/075 ,  Y02T10/126 ,  Y02T50/672

    摘要： The present invention relates generally or preferably to pulsed hypersonic compression waves and more particularly to shaped charge devices using pulsed hypersonic compression waves to create thrust, two-cycle internal and external combustion engines, rotary machines and more specifically to internal and external rotary combustion engines, fluid compressors, vacuum pumps, and drive turbines for expandable gases or pressurized fluid and water, as well as hydrogen.

    摘要翻译： 本发明总体上或优选地涉及脉冲超音速压缩波，更具体地涉及使用脉冲超音速压缩波来形成推力，双循环内部和外部内燃机，旋转机器，更具体地涉及内部和外部旋转燃烧发动机的成形充电装置， 流体压缩机，真空泵和用于可膨胀气体或加压流体和水以及氢气的驱动涡轮机。

    Vertical takeoff and landing aircraft
    49.
    发明授权
    Vertical takeoff and landing aircraft 有权
    垂直起降飞机

    公开(公告)号：US06824097B1

    公开(公告)日：2004-11-30

    申请号：US10649033

    申请日：2003-08-27

    申请人： Richard P. Ouellette ,  Aaron J. Kutzmann

    发明人： Richard P. Ouellette ,  Aaron J. Kutzmann

    IPC分类号： B64D2720

    CPC分类号： F02K7/075 ,  B64C1/1415 ,  B64C29/0058 ,  B64D5/00 ,  B64D27/023 ,  B64D27/20 ,  Y02T50/44 ,  Y02T50/672

    摘要： An aircraft adapted for covert deployment and having low vulnerability to hostile detection and aggression is provided. The aircraft includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The aircraft additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constrained such that the aircraft can be transported within a larger aircraft. This allows for the aircraft to be aerial deployed from the larger aircraft. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, a thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the aircraft is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.

    摘要翻译： 提供了一种适用于秘密部署并且具有较低的敌对侦察和侵略脆弱性的飞机。 飞机包括具有一对侧壁和底部的机身。 侧壁和底部形成一个装甲有效载荷舱。 飞机还包括一对连接到机身的机翼。 机翼具有固定的翼展限制，使得飞机可以在更大的飞机内运输。 这允许飞机从较大的飞机部署空中。 每个侧壁包括向外倾斜的至少一个脉冲喷射器推力增强器（PETA）组。 因此，每个PETA银行产生的推力排气被引导向下并远离有效载荷舱的中心线。 此外，飞机的底部适于允许货物的进出口。 军事部队，从有效载荷湾。

    Methods and apparatus for generating gas turbine engine thrust
    50.
    发明申请
    Methods and apparatus for generating gas turbine engine thrust 有权
    产生燃气轮机发动机推力的方法和装置

    公开(公告)号：US20040118104A1

    公开(公告)日：2004-06-24

    申请号：US10326343

    申请日：2002-12-20

    发明人： John Michael Koshoffer

    IPC分类号： F02K007/02

    CPC分类号： F02K3/08 ,  F02K3/075 ,  F02K7/06 ,  F02K7/075

    摘要： A method enables thrust to be generated from a gas turbine engine using a pulse detonation system is provided. The engine includes an inlet portion and an exhaust portion, and the pulse detonation system includes a multi-staged pulse detonation augmentor including predetonator. The method comprises supplying a less than stoichiometric fuel/air mixture to the pulse detonation system during a first operating stage, detonating the fuel/air mixture with the predetonator to increase the temperature and pressure within the engine and to generate engine thrust, and supplying additional fuel and air to the pulse detonation system during a second operating stage.

    摘要翻译： 提供了一种使用脉冲爆震系统从燃气轮机引擎产生推力的方法。 发动机包括入口部分和排气部分，并且脉冲爆震系统包括多级脉冲爆震增强器，包括预引导器。 该方法包括在第一操作阶段向脉冲爆震系统提供小于化学计量的燃料/空气混合物，用预蒸发器引爆燃料/空气混合物，以增加发动机内的温度和压力并产生发动机推力，并提供额外的 燃料和空气在第二操作阶段期间到脉冲爆震系统。