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    Nacelle short inlet for fan blade removal
    11.
    发明授权
    Nacelle short inlet for fan blade removal 有权

    公开(公告)号：US10479519B2

    公开(公告)日：2019-11-19

    申请号：US15378300

    申请日：2016-12-14

    Applicant: United Technologies Corporation

    Inventor： Yuan J. Qiu ,  Steven H. Zysman ,  Robert E. Malecki ,  Wesley K. Lord

    IPC: B64D33/02 ,  F01D25/24 ,  F02K3/06 ,  F02C7/04 ,  B64D27/10 ,  B64D29/00

    Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.

    NACELLE SHORT INLET
    13.
    发明申请
    NACELLE SHORT INLET 审中-公开

    公开(公告)号：US20170298954A1

    公开(公告)日：2017-10-19

    申请号：US15378371

    申请日：2016-12-14

    Applicant: United Technologies Corporation

    Inventor： Yuan J. Qiu ,  Robert E. Malecki ,  Wesley K. Lord

    IPC: F04D29/54 ,  F02K3/06 ,  F04D29/32

    Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.

    GAS TURBINE ENGINE INLET
    14.
    发明申请
    GAS TURBINE ENGINE INLET 审中-公开
    气体涡轮发动机入口

    公开(公告)号：US20160003145A1

    公开(公告)日：2016-01-07

    申请号：US14767396

    申请日：2014-02-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

    IPC: F02C7/04 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04 ,  F01D5/02

    Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

    Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其轴向方向上的入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。

    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
    15.
    发明授权
    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size 有权

    公开(公告)号：US11286811B2

    公开(公告)日：2022-03-29

    申请号：US16391476

    申请日：2019-04-23

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

    IPC: F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.

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