利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

413 条记录 (耗时 0.019 秒)

    LOW DRAG SKIN HEAT EXCHANGER
    93.
    发明申请
    LOW DRAG SKIN HEAT EXCHANGER 审中-公开
    LOW DRAG皮肤热交换器

    公开(公告)号：US20160159466A1

    公开(公告)日：2016-06-09

    申请号：US14959366

    申请日：2015-12-04

    申请人： Parker-Hannifin Corporation

    发明人： David Lee Daggett ,  Randy Utendorf ,  Irwin Lawson

    IPC分类号： B64C23/00 ,  B64C23/06

    CPC分类号： B64C23/005 ,  B64C23/06 ,  B64D33/10 ,  B64D2041/005 ,  Y02T50/162 ,  Y02T90/36

    摘要： The present invention provides a heat exchanger including a heat exchange panel configured to form an exterior surface of the vehicle (e.g. an aircraft), the heat exchange panel having at least a portion made of a thermally conductive material, and one or more vortex generators protruding from the exterior surface and configured to direct airflow to particular areas on the aircraft, which may then prevent large scale airflow separation. The vortex generator also improves the surface mixing of air flowing over the exterior surface of the heat exchange panel.

    摘要翻译： 本发明提供了一种热交换器，其包括被配置为形成车辆的外表面（例如飞行器）的热交换面板，所述热交换面板具有至少一部分由导热材料制成的部分，以及一个或多个涡流发生器突出 从外表面构造成将气流引导到飞机上的特定区域，这可以防止大规模气流分离。 涡流发生器还改善了在热交换面板的外表面上流动的空气的表面混合。

    Device and method for increasing the aerodynamic lift of an aircraft
    96.
    发明授权
    Device and method for increasing the aerodynamic lift of an aircraft 有权
    增加飞机气动升力的装置和方法

    公开(公告)号：US09193444B2

    公开(公告)日：2015-11-24

    申请号：US13855234

    申请日：2013-04-02

    申请人： Airbus Operations GmbH

    发明人： Carsten Weber ,  Markus Fischer ,  Arne Grote ,  Rolf Radespiel ,  Martin Dreyer

    IPC分类号： B64C3/00 ,  B64C23/06 ,  B64C5/12 ,  B64C9/34

    CPC分类号： B64C23/06 ,  B64C5/12 ,  B64C9/34 ,  Y02T50/162 ,  Y02T50/44

    摘要： A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

    摘要翻译： 飞机的电梯装置包括具有外部的飞机机身部分，附接到飞行器机身部分并从飞行器机身部分向外延伸的空气动力提升机身，以及一对可移动地固定的附加物体，其布置在前缘 的空气动力提升体。 附加物体包括空气动力学有效的表面，并且配备有进入的气流以产生冲击空气动力升程体的涡流，从而导致空气动力升降体的升力增加。 因此，电梯主体上的电梯产生有效地受到影响，特别是为了补偿因结冰导致的电梯损失。 附加物体是可移动的，并且可以移动到中性位置，在该位置中它们不会投射到飞机周围的流中，并且因此从流体动力学的角度来看是没有效果的。

    ROTATABLE AERODYNAMIC SURFACE FEATURES FOR WIND TURBINE ROTOR BLADES
    97.
    发明申请
    ROTATABLE AERODYNAMIC SURFACE FEATURES FOR WIND TURBINE ROTOR BLADES 有权
    风力涡轮机叶片可旋转的气动表面特征

    公开(公告)号：US20150204306A1

    公开(公告)日：2015-07-23

    申请号：US14157598

    申请日：2014-01-17

    申请人： General Electric Company

    发明人： Stefan Herr ,  James Robert Tobin

    IPC分类号： F03D7/02 ,  F03D7/04

    CPC分类号： F03D7/022 ,  B64C3/58 ,  B64C23/06 ,  F03D1/0633 ,  F03D1/0641 ,  F03D1/0675 ,  F03D7/0224 ,  F03D7/0232 ,  F03D7/024 ,  F03D7/0252 ,  F03D80/00 ,  F05B2240/122 ,  F05B2240/30 ,  F05B2240/31 ,  F05B2240/313 ,  F05B2260/502 ,  Y02E10/721 ,  Y02E10/723 ,  Y02T50/162

    摘要： The present subject matter directed to a rotor blade assembly for a wind turbine having at least one rotatable aerodynamic surface feature configured thereon. The rotor blade assembly includes a body shell including a pressure side surface and a suction side surface extending between a leading edge and a trailing edge. The aerodynamic surface feature is disposed adjacent to the pressure side surface, the suction side surface, and/or both. In addition, the surface feature may have a generally airfoil-shaped cross section. As such, an actuator can be configured at least partially within an internal volume of the surface feature, the actuator being configured to rotate the surface feature relative to the body shell.

    摘要翻译： 本发明涉及用于风力涡轮机的转子叶片组件，其具有构造在其上的至少一个可旋转的空气动力学表面特征。 转子叶片组件包括主体壳体，其包括压力侧表面和在前缘和后缘之间延伸的吸力侧表面。 空气动力学表面特征设置成邻近压力侧表面，吸力侧表面和/或两者。 此外，表面特征可以具有大致翼型的横截面。 因此，致动器可以至少部分地配置在表面特征的内部体积内，致动器被配置为相对于主体壳旋转表面特征。

    Vortex generation device
    98.
    发明授权
    Vortex generation device 有权
    涡流生成装置

    公开(公告)号：US09079658B2

    公开(公告)日：2015-07-14

    申请号：US12869884

    申请日：2010-08-27

    申请人： Brian R. Smith ,  Patrick J. Yagle

    发明人： Brian R. Smith ,  Patrick J. Yagle

    IPC分类号： B64C1/38 ,  B64C23/06

    CPC分类号： B64C23/06 ,  Y02T50/162

    摘要： A vortex generation device for reducing drag on an upswept aircraft fuselage afterbody and including a vortex generator vane that extends longitudinally from along an outer mold line of the fuselage of an aircraft adjacent an upswept afterbody of the fuselage and that is configured and positioned to reduce drag on an upswept aircraft fuselage afterbody by developing vortices that counteract vortices generated along such an upswept fuselage afterbody. The vane is disposed aft of a side paratrooper jump door of the aircraft fuselage and has a spine and leading end that are faired smoothly into the mold line of the fuselage.

    摘要翻译： 一种涡流发生装置，用于减少上行的飞行器机身后部的阻力，并包括涡流发生器叶片，该涡流发生器叶片沿着机身机身的外部模具线在机身的上升后身体之间纵向延伸，并且被配置和定位成减小阻力 通过开发涡流来抵抗沿着这种上升的机身后身产生的涡流，在一个上升的机身后身上。 叶片位于飞机机身的侧伞式跳伞的后方，并具有顺利进入机身模具线的脊柱和前端。

    VORTEX GENERATORS
    99.
    发明申请
    VORTEX GENERATORS 有权
    VORTEX发电机

    公开(公告)号：US20150090356A1

    公开(公告)日：2015-04-02

    申请号：US14042443

    申请日：2013-09-30

    申请人： The Boeing Company

    发明人： Dan John Clingman ,  Esther Shifra Zidovetzki ,  Randy Lee Macaraeg Mallari

    IPC分类号： F15D1/00

    CPC分类号： F15D1/009 ,  B64C23/005 ,  B64C23/06 ,  Y02T50/162 ,  Y02T50/166 ,  Y10T137/2087

    摘要： Vortex generators are disclosed herein. An example apparatus includes a housing including a surface. The example apparatus also includes a bimorph actuator disposed in the housing. The bimorph actuator includes a first bimorph beam having a first portion fixed relative to the surface. A blade is rotatably coupled to the bimorph actuator, and the bimorph actuator is to rotate the blade to extend a portion of the blade through the surface to generate a vortex in a fluid flowing past the surface.

    摘要翻译： 本文公开涡旋发生器。 示例性装置包括包括表面的壳体。 示例性装置还包括设置在壳体中的双压电晶片致动器。 双压电晶片致动器包括具有相对于表面固定的第一部分的第一双压电晶片。 叶片可旋转地联接到双压电晶片致动器，并且双压电晶片致动器将旋转叶片以使叶片的一部分延伸穿过该表面以在流过该表面的流体中产生涡流。

    Engine pylon comprising a vortex generator, and method for the production thereof
    100.
    发明授权
    Engine pylon comprising a vortex generator, and method for the production thereof 有权
    包括涡流发生器的发动机塔架及其制造方法

    公开(公告)号：US08936213B2

    公开(公告)日：2015-01-20

    申请号：US13508283

    申请日：2010-10-27

    申请人： Steve Bedoin ,  Cyril Bonnaud

    发明人： Steve Bedoin ,  Cyril Bonnaud

    IPC分类号： B64D27/00 ,  B64C7/02 ,  B64C23/06 ,  B64D29/02 ,  F02C7/20

    CPC分类号： B64C7/02 ,  B64C23/06 ,  B64D29/02 ,  F02C7/20 ,  F05D2240/127 ,  Y02T50/162 ,  Y02T50/671 ,  Y10T29/49231

    摘要： The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

    摘要翻译： 本发明涉及一种用于制造安装在发动机（1）和飞行器机翼（6）之间的发动机塔架（7）的方法，所述方法包括：将主塔架（8）安装在主结构（9）周围， 所述箱体具有大致长方形的形状，在飞行时沿着所述箱体形成空气边界层（C）; 将至少一个涡流发生器（2）安装到所述塔架箱上，使得所述边界层的厚度（e）改变; 并且基于边界层的厚度改变和涡流发生器的位置预先确定塔的形状。