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22 条记录 (耗时 0.021 秒)

    Divergent trailing-edge airfoil
    1.
    发明授权
    Divergent trailing-edge airfoil 失效
    发散的后缘翼型

    公开(公告)号：US4858852A

    公开(公告)日：1989-08-22

    申请号：US56250

    申请日：1987-06-01

    申请人： Preston A. Henne ,  Robert D. Gregg, III

    发明人： Preston A. Henne ,  Robert D. Gregg, III

    IPC分类号： B64C3/14

    CPC分类号： B64C3/14 ,  B64C2003/149 ,  Y02T50/12

    摘要： A special contour near the trailing edge of an airfoil which improves the airfoil effectiveness. The contour is a combination of a blunt airfoil base, a local region of high surface curvature, typically on the airfoil lower surface, and upper surface and lower surface trailing edge slopes that diverge from each other.

    摘要翻译： 在翼型的后缘附近有一个特殊的轮廓，提高了翼型的有效性。 轮廓是平头翼型基座，高表面曲率的局部区域，通常在翼型下表面上，以及彼此分开的上表面和下表面后缘的组合。

    Mitigation of unsteady peak fan blade and disc stresses in turbofan engines through the use of flow control devices to stabilize boundary layer characteristics
    5.
    发明授权
    Mitigation of unsteady peak fan blade and disc stresses in turbofan engines through the use of flow control devices to stabilize boundary layer characteristics 有权
    通过使用流量控制装置来稳定边界层特性，减轻涡轮风扇发动机中不稳定的峰值风扇叶片和圆盘应力

    公开(公告)号：US07878759B2

    公开(公告)日：2011-02-01

    申请号：US10710723

    申请日：2004-07-30

    申请人： Robert J. Mills ,  Preston A. Henne

    发明人： Robert J. Mills ,  Preston A. Henne

    IPC分类号： F01D5/14

    CPC分类号： F04D29/384 ,  F01D5/145 ,  F04D29/668 ,  F04D29/681 ,  F05D2240/31 ,  F15D1/12 ,  Y02T50/673

    摘要： Method and apparatus for providing a turbofan blade 40 adapted to initiate and control a boundary layer transition at a side surface of the blade 40 during operation as a component in a turbofan assembly 35. The turbofan blade 40 includes a leading edge 55, a trailing edge 58, and two side surfaces including a high-pressure side surface 49 and a low-pressure side surface 52. At least one of the two side surfaces has an essentially smooth surface portion 61 located between the leading and trailing edges, and the essentially smooth surface portion is interrupted by a surface deviation 64. The surface deviation is configured to fix a positionally unstable laminar to turbulent boundary layer transition 24 at a location toward the trailing edge from the surface deviation during operation of the turbofan blade in the turbofan assembly. In this manner, fatigue inducing and/or structurally damaging unsteady aerodynamic forces experienced upon the blade and/or fan disc during operation are controlled, and the resultant fluctuating fan blade and disc peak stresses are mitigated.

    摘要翻译： 用于提供涡轮风扇叶片40的方法和装置，其适用于在作为涡扇风扇组件35中的部件操作期间启动和控制在叶片40的侧表面处的边界层转变。涡扇叶片40包括前缘55，后缘 58和包括高压侧表面49和低压侧表面52的两个侧表面。两个侧表面中的至少一个具有位于前缘和后缘之间的基本平滑的表面部分61，并且基本上平滑 表面部分被表面偏差64中断。表面偏差被配置为在涡轮风扇组件中的涡轮风扇叶片的操作期间，将位置不稳定的层流固定在位于朝向后缘的位置处的湍流边界层过渡部24。 以这种方式，控制在操作期间在叶片和/或风扇盘上经历的疲劳诱导和/或结构损坏的非稳态空气动力，并且减轻所产生的波动的风扇叶片和盘峰值应力。

    Sub-scale sonic boom modeling
    6.
    发明授权
    Sub-scale sonic boom modeling 有权
    小型音响造型

    公开(公告)号：US07634941B2

    公开(公告)日：2009-12-22

    申请号：US12010042

    申请日：2008-01-18

    申请人： Preston A. Henne ,  Donald C. Howe ,  Robert R. Wolz

    发明人： Preston A. Henne ,  Donald C. Howe ,  Robert R. Wolz

    IPC分类号： G01M9/00

    CPC分类号： G01M9/06

    摘要： A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale version of the aircraft of interest at a supersonic Mach number and at an altitude that are respectively different from the Mach number and the altitude associated with the operating point of interest. The Mach number and altitude at which the sub-scale aircraft is operated is selected such that peak overpressure generated by the sub-scale aircraft and time to rise to peak overpressure are the same as peak overpressure and time to rise to peak overpressure caused by operating the aircraft of interest at the operating point of interest.

    摘要翻译： 一种用于对由感兴趣的飞机在特定超音速马赫数/高度作业点处飞行产生的声学特征进行建模的方法。 该方法包括以超音速马赫数和分别与马赫数和与感兴趣的运行点相关联的高度不同的高度操作作为感兴趣的飞机的子规模版本的次级飞行器。 选择小型飞机运行的马赫数和高度，使得次级飞机产生的峰值超压和达到峰值超压的时间与峰值超压和上升到由运行引起的超压峰值的时间相同 感兴趣的操作点的飞机。

    Ice prevention device for airfoils
    8.
    发明授权
    Ice prevention device for airfoils 失效
    机翼防冰装置

    公开(公告)号：US5322246A

    公开(公告)日：1994-06-21

    申请号：US743667

    申请日：1991-08-12

    申请人： Preston A. Henne ,  Walter S. Boronow ,  Samuel L. Wong ,  Willard D. Himebaugh

    发明人： Preston A. Henne ,  Walter S. Boronow ,  Samuel L. Wong ,  Willard D. Himebaugh

    IPC分类号： B64D15/00

    CPC分类号： B64D15/00

    摘要： An aft facing step situated across the span of an airfoil. A chemical or thermal deicing or running wet anti-icing device is located in or on the airfoil upstream of the step, and causes water to run back towards the step. The step suddenly reduces the thickness of the airfoil chord section, which causes a disturbance in the boundary layer across the span of the airfoil downstream of the step. The aforementioned disturbance causes runback water to form droplets and be blown clear of the airfoil surface downstream of the step, thereby preventing ice from being formed on the airfoil surface downstream of the step.

    摘要翻译： 位于翼型跨度跨过的后方朝向台阶。 化学或热除冰或运行的湿式防冰装置位于台阶上游的翼型件中或其上，并使水回向台阶。 该步骤突然减小翼型弦部分的厚度，这导致跨越台阶下游的翼型跨度的边界层的扰动。 上述扰动导致回流水形成液滴，并且在步骤下游从翼型表面吹出，从而防止在台阶下游的翼型表面上形成冰。