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    Gas turbine engine airfoils having multimodal thickness distributions
    1.
    发明授权
    Gas turbine engine airfoils having multimodal thickness distributions 有权

    公开(公告)号：US10895161B2

    公开(公告)日：2021-01-19

    申请号：US15338026

    申请日：2016-10-28

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

    IPC: F01D9/04 ,  F01D5/16 ,  F01D5/14

    Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions are provided. In one embodiment, the GTE airfoil includes an airfoil tip, an airfoil root opposite the airfoil tip in a spanwise direction, and first and second airfoil halves extending between the airfoil tip and the airfoil root. The first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in a thickness direction substantially perpendicular to the spanwise direction. The first multimodal thickness distribution may be defined by multiple locally-thickened airfoil regions, which are interspersed with multiple locally-thinned airfoil regions. The second airfoil half may or may not have a multimodal thickness distribution. By imparting at least one airfoil half with such a multimodal thickness distribution, targeted mechanical properties of the GTE airfoil may be enhanced with relatively little impact on aerodynamic performance.

    FORWARD-SWEPT IMPELLERS AND GAS TURBINE ENGINES EMPLOYING THE SAME
    3.
    发明申请
    FORWARD-SWEPT IMPELLERS AND GAS TURBINE ENGINES EMPLOYING THE SAME 有权
    前进式驱动器和使用其的气动涡轮发动机

    公开(公告)号：US20160238018A1

    公开(公告)日：2016-08-18

    申请号：US14623761

    申请日：2015-02-17

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Richard David Conner ,  Michael Todd Barton ,  Yoseph Gebre-Giorgis ,  Harry Lester Kington ,  John Repp

    IPC: F04D29/28 ,  F01D9/04 ,  F01D5/22 ,  F04D29/32

    CPC classification number: F04D29/284 ,  F01D5/225 ,  F01D9/04 ,  F02C3/09 ,  F05D2250/38 ,  F05D2260/941 ,  Y02T50/671

    Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.

    Abstract translation: 如同包含前掠式叶轮的燃气涡轮发动机的实施例一样，提供了前掠式叶轮的实施例。 在一个实施例中，燃气涡轮发动机包括安装在轴上的轴和向前扫掠的叶轮。 前掠式叶轮又包括内侧叶轮部分，外侧叶轮部分，其包围内侧叶轮部分，以及多个轮毂流动路径，其沿前掠式叶轮从内侧叶轮部分延伸到外侧叶轮部分。 多个轮毂流动路径各自具有沿着与流路出口相切的直线沿向前方向倾斜的流路出口。

    GAS TURBINE ENGINE AIRFOILS HAVING MULTIMODAL THICKNESS DISTRIBUTIONS
    7.
    发明申请
    GAS TURBINE ENGINE AIRFOILS HAVING MULTIMODAL THICKNESS DISTRIBUTIONS 有权

    公开(公告)号：US20210102472A1

    公开(公告)日：2021-04-08

    申请号：US17109484

    申请日：2020-12-02

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Constantinos Vogiatzis ,  Yoseph Gebre-Giorgis

    IPC: F01D9/04 ,  F01D5/16 ,  F01D5/14

    Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions include an airfoil tip, and an airfoil root opposite the airfoil tip in a spanwise direction. The GTE airfoil has a first, second and third locally-thickened region, with the first locally-thickened region defined at the airfoil root. A maximum thickness of each chord between the airfoil root and the airfoil tip transitions toward the leading edge between the first locally-thickened region and the second locally-thickened region, and the third locally-thickened region extends in the spanwise direction. A chord line that extends through the third locally-thickened region contains a first local thickness maxima and a second local thickness maxima interspersed with at least two local thickness minima, and the first local thickness maxima is defined by the third locally-thickened region and is greater than the second local thickness maxima.

    Core-protecting fan modules and turbofan engines containing the same
    8.
    发明授权
    Core-protecting fan modules and turbofan engines containing the same 审中-公开

    公开(公告)号：US10670040B2

    公开(公告)日：2020-06-02

    申请号：US15439430

    申请日：2017-02-22

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Nick Nolcheff ,  John Repp ,  Jeffrey Hayes ,  John A Gunaraj ,  Yoseph Gebre-Giorgis

    IPC: F04D29/32 ,  F04D29/54 ,  F04D29/34 ,  F01D5/14 ,  F01D5/34 ,  F02K3/06 ,  F01D5/02 ,  F02C7/05 ,  B64D33/02 ,  B64C11/14

    Abstract: Embodiments of a core-protecting fan module are provided, as are embodiments of a turbofan engine containing such a fan module. In an embodiment, the core-protecting fan module contains a nose member, a fan rotor downstream of the nose member, a full span stator downstream of the fan rotor, and a splitter structure downstream of the fan rotor. The fan rotor includes a plurality of fan blades, which extends from a rotor hub and which is angularly spaced about a rotational axis. Certain fundamental angular relationships are observed between the angles formed by rotational axis, the nose member, the fan rotor, and a leading edge of the splitter structure to reduce contaminant ingestion by the core flow path and to promote moisture shedding to reduce susceptibility to icing within the fan module, while further avoiding or minimizing negative impacts to other structural and functional aspects of the turbofan engine.

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