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    MICRO LATTICE HYBRID COMPOSITE FAN BLADE
    4.
    发明申请
    MICRO LATTICE HYBRID COMPOSITE FAN BLADE 审中-公开

    公开(公告)号：US20180038385A1

    公开(公告)日：2018-02-08

    申请号：US15226147

    申请日：2016-08-02

    Applicant: United Technologies Corporation

    Inventor： David A. Welch

    IPC: F04D29/38 ,  F04D19/00 ,  B22F5/04 ,  F04D29/02 ,  B22F3/105 ,  F02K3/06 ,  F04D29/32

    Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.

    SHORT INLET WITH INTEGRATED LINER ANTI-ICING
    5.
    发明申请
    SHORT INLET WITH INTEGRATED LINER ANTI-ICING 审中-公开

    公开(公告)号：US20170298821A1

    公开(公告)日：2017-10-19

    申请号：US15131145

    申请日：2016-04-18

    Applicant: United Technologies Corporation

    Inventor： David A. Welch

    IPC: F02C7/047 ,  F02C7/24 ,  F02C7/30

    Abstract: A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed.

    Airfoil with integral platform for gas turbine engines
    6.
    发明授权
    Airfoil with integral platform for gas turbine engines 有权

    公开(公告)号：US11428105B2

    公开(公告)日：2022-08-30

    申请号：US16846590

    申请日：2020-04-13

    Applicant: United Technologies Corporation

    Inventor： David A. Welch ,  Michael Raymond LaFavor

    IPC: F01D5/30 ,  F01D5/20 ,  F01D5/18 ,  F01D5/14

    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending 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, and the airfoil section defining a pressure side and a suction side separated in a circumferential direction. A platform includes a first and second platform portions attached to the root section. Each of the first and second platform portions includes a shoe section and a platform section extending in the circumferential direction from the shoe section to establish a gas path surface, and the shoe sections of the first and second platforms are circumferentially arranged on opposed sides of the root section to capture the root section in a root cavity established between the shoe sections. A method of assembly is also disclosed.

    AIRFOIL WITH INTEGRAL PLATFORM FOR GAS TURBINE ENGINES
    7.
    发明申请
    AIRFOIL WITH INTEGRAL PLATFORM FOR GAS TURBINE ENGINES 有权

    公开(公告)号：US20210317747A1

    公开(公告)日：2021-10-14

    申请号：US16846590

    申请日：2020-04-13

    Applicant: United Technologies Corporation

    Inventor： David A. Welch ,  Michael Raymond LaFavor

    IPC: F01D5/20 ,  F01D5/18

    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending 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, and the airfoil section defining a pressure side and a suction side separated in a circumferential direction. A platform includes a first and second platform portions attached to the root section. Each of the first and second platform portions includes a shoe section and a platform section extending in the circumferential direction from the shoe section to establish a gas path surface, and the shoe sections of the first and second platforms are circumferentially arranged on opposed sides of the root section to capture the root section in a root cavity established between the shoe sections. A method of assembly is also disclosed.

    Short inlet with integrated liner anti-icing
    9.
    发明授权
    Short inlet with integrated liner anti-icing 有权

    公开(公告)号：US10533497B2

    公开(公告)日：2020-01-14

    申请号：US15131145

    申请日：2016-04-18

    Applicant: United Technologies Corporation

    Inventor： David A. Welch

    IPC: F02C7/047 ,  F02C7/24 ,  F02C6/08 ,  F02C7/30

    Abstract: A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed.

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