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    MODAL NOISE REDUCTION FOR GAS TURBINE ENGINE
    12.
    发明申请
    MODAL NOISE REDUCTION FOR GAS TURBINE ENGINE 有权

    公开(公告)号：US20220341439A1

    公开(公告)日：2022-10-27

    申请号：US17689260

    申请日：2022-03-08

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： David A. Topol

    IPC: F04D29/66 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/04 ,  F04D29/32 ,  F01D5/26 ,  F04D29/54

    Abstract: A gas turbine engine according to an aspect of the present disclosure includes, among other things, a propulsor section, a compressor section including a first compressor and a second compressor, and a turbine section including a first turbine and a second turbine. The first compressor includes a plurality of arrays of airfoils defining a plurality of compressor stages. A number of airfoils in each downstream array of the plurality of arrays is a factor (F) of a number of airfoils in a respective immediately upstream array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for each of the downstream arrays of the first compressor.

    Triangular-frame connection between fan case and core housing in a gas turbine engine
    13.
    发明授权
    Triangular-frame connection between fan case and core housing in a gas turbine engine 有权

    公开(公告)号：US11708772B2

    公开(公告)日：2023-07-25

    申请号：US17701010

    申请日：2022-03-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F01D25/24 ,  F01D25/28 ,  F01D9/04

    CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D25/28 ,  F05D2240/14 ,  F05D2250/11 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

    Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

    H-frame connection between fan case and core housing in a gas turbine engine
    14.
    发明授权
    H-frame connection between fan case and core housing in a gas turbine engine 有权

    公开(公告)号：US11686220B2

    公开(公告)日：2023-06-27

    申请号：US17700992

    申请日：2022-03-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F01D25/28 ,  F01D25/24 ,  F01D9/04

    CPC classification number: F01D25/28 ,  F01D9/041 ,  F01D25/24 ,  F05D2240/126 ,  F05D2240/14 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

    Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of H-frame connecting members rigidly connected to the fan case, and to the core engine. The H-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions which are generally parallel to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

    RADIAL STRUT FRAME CONNECTION BETWEEN FAN CASE AND CORE HOUSING IN A GAS TURBINE ENGINE
    15.
    发明公开
    RADIAL STRUT FRAME CONNECTION BETWEEN FAN CASE AND CORE HOUSING IN A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230151777A1

    公开(公告)日：2023-05-18

    申请号：US18098920

    申请日：2023-01-19

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F02K3/06 ,  F02C3/04

    CPC classification number: F02K3/06 ,  F02C3/04 ,  F05D2260/96 ,  F05D2220/36 ,  F05D2240/12

    Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine including a plurality of radial struts rigidly connected to the fan case, and to the core engine. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

    H-FRAME CONNECTION BETWEEN FAN CASE AND CORE HOUSING IN A GAS TURBINE ENGINE
    16.
    发明公开
    H-FRAME CONNECTION BETWEEN FAN CASE AND CORE HOUSING IN A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230151742A1

    公开(公告)日：2023-05-18

    申请号：US17700992

    申请日：2022-03-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F01D25/28 ,  F01D25/24 ,  F01D9/04

    CPC classification number: F01D25/28 ,  F01D25/24 ,  F01D9/041 ,  F05D2240/126 ,  F05D2240/14 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

    Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of H-frame connecting members rigidly connected to the fan case, and to the core engine. The H-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions which are generally parallel to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

    Radial strut frame connection between fan case and core housing in a gas turbine engine
    17.
    发明授权
    Radial strut frame connection between fan case and core housing in a gas turbine engine 有权

    公开(公告)号：US11608796B1

    公开(公告)日：2023-03-21

    申请号：US17701026

    申请日：2022-03-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F02C7/20 ,  F02K3/06 ,  F02C3/04

    Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine including a plurality of radial struts rigidly connected to the fan case, and to the core engine. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

    Frame connection between fan case and core housing in a gas turbine engine
    18.
    发明授权
    Frame connection between fan case and core housing in a gas turbine engine 有权

    公开(公告)号：US11555420B1

    公开(公告)日：2023-01-17

    申请号：US17407275

    申请日：2021-08-20

    Applicant: Raytheon Technologies Corporation

    Inventor： Anthony R. Bifulco ,  David A. Topol

    IPC: F01D25/28 ,  F01D25/24 ,  F01D9/06

    Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.

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