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    HIGH SPEED ROTOR BLADE DESIGN
    4.
    发明公开
    HIGH SPEED ROTOR BLADE DESIGN 审中-公开

    公开(公告)号：US20230322373A1

    公开(公告)日：2023-10-12

    申请号：US17706531

    申请日：2022-03-28

    申请人： LOCKHEED MARTIN CORPORATION

    发明人： Byung-Young Min ,  Vera Klimchenko ,  Annie Gao ,  Alexander F. Dunn ,  Claude George Matalanis ,  Brian Ernest Wake

    IPC分类号： B64C27/473 ,  B64C27/467

    CPC分类号： B64C27/467 ,  B64C27/473

    摘要： A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

    LOW-NOISE BLADE FOR AN OPEN ROTOR
    5.
    发明公开
    LOW-NOISE BLADE FOR AN OPEN ROTOR 审中-公开

    公开(公告)号：US20230249810A1

    公开(公告)日：2023-08-10

    申请号：US18169757

    申请日：2023-02-15

    申请人： General Electric Company

    发明人： Kishore Ramakrishnan ,  Valeria Andreoli ,  Daniel L. Tweedt

    IPC分类号： B64C27/473 ,  B64C27/467

    CPC分类号： B64C27/473 ,  B64C27/467

    摘要： A blade for an open rotor includes a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein for at least 30% of a span of the blade, the meanline of the airfoil section is shaped such that a relative curvature parameter is greater than 1.2 in a first region, less than 0.75 in a second region, and greater than 0.9 in a third region, wherein the relative curvature parameter of a region is defined by Δζn/Δζtot/Δ(x/c)n wherein ζ corresponds to the inverse tangent of the slope of a meanline curve, subscript n indicates the region, and x/c is a chordwise location normalized by the chord and wherein the first region comprises at least x/c=0.0 to 0.15 and the third region comprises at least x/c=0.80 to 1.0.

    Airfoils and Machines Incorporating Airfoils
    6.
    发明申请
    Airfoils and Machines Incorporating Airfoils 有权

    公开(公告)号：US20220348270A1

    公开(公告)日：2022-11-03

    申请号：US17841945

    申请日：2022-06-16

    申请人： ESS 2 Tech, LLC

    发明人： Michael Suk ,  David A. Shoffler

    IPC分类号： B62D35/00 ,  B64C3/14 ,  F01D5/14 ,  F04D29/38 ,  B64C11/18 ,  F04D29/28 ,  B64C27/467 ,  F04D29/42 ,  F15D1/00 ,  F04D29/68

    摘要： Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

    Bistable pitch propeller system with bidirectional propeller rotation
    9.
    发明授权
    Bistable pitch propeller system with bidirectional propeller rotation 有权

    公开(公告)号：US11254419B2

    公开(公告)日：2022-02-22

    申请号：US17001391

    申请日：2020-08-24

    申请人： Kitty Hawk Corporation

    发明人： Damon Vander Lind ,  Todd Reichert

    IPC分类号： B64C11/32 ,  B64C11/34 ,  B64C11/18 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02

    摘要： A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

    Aircraft rotor blade sleeve having a protuberance in its rear zone, and a rotor provided with such a sleeve
    10.
    发明授权
    Aircraft rotor blade sleeve having a protuberance in its rear zone, and a rotor provided with such a sleeve 有权

    公开(公告)号：US11192644B2

    公开(公告)日：2021-12-07

    申请号：US16067188

    申请日：2017-06-16

    申请人： AIRBUS HELICOPTERS

    发明人： Damien Desvigne ,  David Alfano

    IPC分类号： B64C27/48 ,  B64C27/467 ,  B64C3/14

    摘要： A sleeve connecting a blade to the hub of a rotor of a rotary wing aircraft. The sleeve has a leading edge and a trailing edge, together with a protuberance arranged on the trailing edge. The dimensions of the protuberance are linked to the dimensions of the sleeve. The presence of the protuberance serves to improve the aerodynamic behavior of the sleeve and of the rotor during rotation of the rotor while the aircraft is moving forwards, both when the sleeve is advancing and when it is retreating. The presence of the protuberance also serves to reduce the vibration generated by a wake of the rotor on a tail boom or on a horizontal and/or vertical stabilizer of the aircraft.