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    CONICAL FAN HUB AND METHOD FOR REDUCING BLADE OFF LOADS
    12.
    发明申请
    CONICAL FAN HUB AND METHOD FOR REDUCING BLADE OFF LOADS 审中-公开

    公开(公告)号：US20190063452A1

    公开(公告)日：2019-02-28

    申请号：US15689946

    申请日：2017-08-29

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F04D29/32 ,  F04D29/34 ,  F01D21/04

    Abstract: A conical hub for a fan of a gas turbine engine is provided. The conical hub having: a plurality of attachment features located on an outer circumferential surface of the conical hub, wherein at least some of the plurality attachment features are axially aligned with each other and at least some of the plurality of attachment features are off set from each other, and wherein each of the plurality of attachment features have an opening configured to receive a portion of a pin; and the outer circumferential surface of the conical hub increases in diameter with respect to an axis of the conical hub in a forward to aft direction of the conical hub.

    Rotor assembly with active damping for gas turbine engines
    13.
    发明授权
    Rotor assembly with active damping for gas turbine engines 有权

    公开(公告)号：US11136888B2

    公开(公告)日：2021-10-05

    申请号：US16163690

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey ,  David A. Welch

    IPC: F01D5/14 ,  F01D5/16 ,  F01D5/02

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction, and the airfoil section includes a metallic sheath that defines an internal cavity receiving a composite core. The root section defines at least one bore dimensioned to receive a retention pin. At least one damping element is received in the internal cavity and that selectively causes the airfoil section to stiffen.

    Hybrid airfoil for gas turbine engines
    14.
    发明授权
    Hybrid airfoil for gas turbine engines 有权

    公开(公告)号：US10822969B2

    公开(公告)日：2020-11-03

    申请号：US16163607

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core. The core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. Each one of the first and second ligaments includes at least one interface portion in the root section, and at least one interface portion of the first ligament and the at least one interface portion of the second ligament define respective sets of bores aligned to receive a common retention pin.

    HYBRID AIRFOIL FOR GAS TURBINE ENGINES
    15.
    发明申请
    HYBRID AIRFOIL FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20200123914A1

    公开(公告)日：2020-04-23

    申请号：US16163607

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core. The core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. Each one of the first and second ligaments includes at least one interface portion in the root section, and at least one interface portion of the first ligament and the at least one interface portion of the second ligament define respective sets of bores aligned to receive a common retention pin.

    Fan hub attachment for leading and trailing edges of fan blades
    17.
    发明授权
    Fan hub attachment for leading and trailing edges of fan blades 有权

    公开(公告)号：US10280767B2

    公开(公告)日：2019-05-07

    申请号：US15689953

    申请日：2017-08-29

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  B64C11/04 ,  F02C7/04

    Abstract: In one embodiment, a hub for a fan of a gas turbine engine is provided. The hub having: a plurality of attachment features located on an outer circumferential surface of the hub, wherein at least some of the plurality attachment features extend radially away from the outer circumferential surface and are axially aligned with each other and at least some of the plurality of attachment features extending radially away from the outer circumferential surface and are off set from each other, and wherein the plurality of attachment features have an opening configured to receive a portion of a pin; and wherein at least some of the plurality of attachment features are located on a forward leading edge of the hub.

    FAN HUB ATTACHMENT FOR LEADING AND TRAILING EDGES OF FAN BLADES
    19.
    发明申请
    FAN HUB ATTACHMENT FOR LEADING AND TRAILING EDGES OF FAN BLADES 审中-公开

    公开(公告)号：US20190063236A1

    公开(公告)日：2019-02-28

    申请号：US15689953

    申请日：2017-08-29

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  B64C11/04

    Abstract: In one embodiment, a hub for a fan of a gas turbine engine is provided. The hub having: a plurality of attachment features located on an outer circumferential surface of the hub, wherein at least some of the plurality attachment features extend radially away from the outer circumferential surface and are axially aligned with each other and at least some of the plurality of attachment features extending radially away from the outer circumferential surface and are off set from each other, and wherein the plurality of attachment features have an opening configured to receive a portion of a pin; and wherein at least some of the plurality of attachment features are located on a forward leading edge of the hub.

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