AUGMENTED DRIVE OF COMPRESSORS VIA DIFFERENTIAL AND MULTISTAGE TURBINE

    公开(公告)号:US20240018901A1

    公开(公告)日:2024-01-18

    申请号:US18364422

    申请日:2023-08-02

    CPC classification number: F02C3/113 F02C3/14 F02C9/56 F02K3/10 F02C9/00

    Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

    SPLITTER AND GUIDE VANE ARRANGEMENT FOR GAS TURBINE ENGINES

    公开(公告)号:US20230407817A1

    公开(公告)日:2023-12-21

    申请号:US18461709

    申请日:2023-09-06

    CPC classification number: F02K3/077 F02K3/075 F02K1/72

    Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. An aftmost row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths.

    HYBRID GAS TURBOFAN POWERED SUB-IDLE DESCENT MODE

    公开(公告)号:US20250163823A1

    公开(公告)日:2025-05-22

    申请号:US19033023

    申请日:2025-01-21

    Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.

    Augmented drive of compressors via differential and multistage turbine

    公开(公告)号:US12173644B2

    公开(公告)日:2024-12-24

    申请号:US18364422

    申请日:2023-08-02

    Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

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