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    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN
    41.
    发明申请
    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN 审中-公开

    公开(公告)号：US20190161167A1

    公开(公告)日：2019-05-30

    申请号：US15860280

    申请日：2018-01-02

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

    AEROELASTICALLY TAILORED PROPELLERS FOR NOISE REDUCTION AND IMPROVED EFFICIENCY IN A TURBOMACHINE
    44.
    发明申请
    AEROELASTICALLY TAILORED PROPELLERS FOR NOISE REDUCTION AND IMPROVED EFFICIENCY IN A TURBOMACHINE 审中-公开
    用于减少噪音和提高涡轮发动机效率的全自动定制螺旋桨

    公开(公告)号：US20150344127A1

    公开(公告)日：2015-12-03

    申请号：US14292873

    申请日：2014-05-31

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: B64C11/50

    CPC classification number: B64C11/18 ,  B64D2027/005 ,  Y02T50/66

    Abstract: Aeroelastically tailored propellers for noise reduction and improved efficiency in a turbomachine are provided including one or more upstream blades and one or more downstream blades disposed downstream relative to the one or more upstream blades. Each of the one or more upstream blades and the one or more downstream blades are aeroelastically tailored such that the one or more downstream blades include a greater degree of effective clipping during a second condition than at a first condition. Each blade among the one or more upstream blades comprises one or more geometric parameters. Each blade among the one or more downstream blades comprises one or more geometric parameters. In addition, an open rotor aircraft gas turbine engine assembly including the aeroelastically tailored propellers and a method of decreasing noise and improving efficiency in a turbomachine are disclosed.

    Abstract translation: 提供用于噪声降低和提高涡轮机效率的气动弹性定制推进器，包括一个或多个上游叶片和相对于一个或多个上游叶片设置在下游的一个或多个下游叶片。 所述一个或多个上游叶片和所述一个或多个下游叶片中的每一个被气动地定制，使得所述一个或多个下游叶片在第二状态期间比在第一条件下包括更大程度的有效限幅。 一个或多个上游叶片中的每个叶片包括一个或多个几何参数。 一个或多个下游叶片中的每个叶片包括一个或多个几何参数。 另外，公开了一种包括气动定型螺旋桨的开放式转子飞机燃气涡轮发动机组件以及降低噪声并提高涡轮机效率的方法。

    UNDUCTED AIRFOIL ASSEMBLY
    45.
    发明申请
    UNDUCTED AIRFOIL ASSEMBLY 有权

    公开(公告)号：US20250154872A1

    公开(公告)日：2025-05-15

    申请号：US19021666

    申请日：2025-01-15

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Daniel Lawrence Tweedt

    IPC: F01D5/14

    Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.

    Reverse thrust turbofan engine
    46.
    发明授权
    Reverse thrust turbofan engine 有权

    公开(公告)号：US12286941B2

    公开(公告)日：2025-04-29

    申请号：US18299102

    申请日：2023-04-12

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Thomas Malkus ,  Kishore Ramakrishnan

    IPC: F02K1/66 ,  F02K1/32

    Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.

    OUTLET GUIDE VANE ASSEMBLY FOR A TURBOFAN ENGINE
    47.
    发明公开
    OUTLET GUIDE VANE ASSEMBLY FOR A TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20240309769A1

    公开(公告)日：2024-09-19

    申请号：US18674010

    申请日：2024-05-24

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Ravish Karve ,  Sara Elizabeth Carle ,  Trevor Howard Wood

    IPC: F01D9/04 ,  F01D25/28

    CPC classification number: F01D9/041 ,  F01D25/28 ,  F05D2220/323 ,  F05D2250/37 ,  F05D2260/961

    Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including NOGV number of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by NOGV, and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.

    TURBOMACHINE AND METHOD OF ASSEMBLY
    50.
    发明公开
    TURBOMACHINE AND METHOD OF ASSEMBLY 审中-公开

    公开(公告)号：US20240295224A1

    公开(公告)日：2024-09-05

    申请号：US18656056

    申请日：2024-05-06

    Applicant: General Electric Company

    Inventor： Jixian Yao ,  Trevor Howard Wood ,  Kishore Ramakrishnan ,  William Joseph Solomon ,  Giridhar Jothiprasad ,  Nicholas Joseph Kray

    IPC: F04D29/38 ,  F04D19/00

    CPC classification number: F04D29/384 ,  F04D19/002

    Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a composite blade including a composite airfoil section having an airfoil leading edge and an airfoil trailing edge, a root attached to the composite airfoil section, and a blade shank therebetween. A metallic leading edge shield covers an axially extending portion of the composite airfoil section including at least a portion of the airfoil leading edge and covers a radially and chordwise extending portion of the airfoil leading edge of the blade shank. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

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