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    Supersonic aircraft turbofan engine
    2.
    发明授权
    Supersonic aircraft turbofan engine 有权

    公开(公告)号：US11884414B2

    公开(公告)日：2024-01-30

    申请号：US16451459

    申请日：2019-06-25

    申请人： ROLLS-ROYCE plc

    发明人： Robert J Corin ,  John R Whurr

    IPC分类号： B64D33/02 ,  B64C30/00 ,  F02C7/04 ,  F02K1/08 ,  F02K1/38 ,  F02K3/075

    CPC分类号： B64D33/02 ,  B64C30/00 ,  F02C7/04 ,  F02K1/08 ,  B64D2033/026 ,  B64D2033/0286 ,  F02K1/386 ,  F02K3/075 ,  F05D2220/80 ,  F05D2250/51

    摘要： Engine has core compressor, combustor and turbine, fan located upstream of core and supersonic intake for slowing down incoming air at inlet formed by intake, bypass duct surrounding engine core, fan generates airflow to engine core and bypass airflow through bypass duct. Engine has mixer for exhaust gas flow exiting engine core, bypass airflow exiting bypass duct, thrust nozzle for discharging mixed flows, and controller for thrust produced by engine. To change level of engine thrust between transonic push operation and supersonic cruise operation, controller adjusts one or more components which vary relative areas available for hot exhaust gas flow and cold bypass airflow at mixer while holding fan inlet non-dimensional mass flow w √{square root over ( )} T/P substantially constant, where w is mass flow of incoming air at fan inlet, T is stagnation temperature of incoming air at fan inlet and P is stagnation pressure of incoming air at fan inlet.

    SPLITTER AND GUIDE VANE ARRANGEMENT FOR GAS TURBINE ENGINES
    4.
    发明公开
    SPLITTER AND GUIDE VANE ARRANGEMENT FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20230407817A1

    公开(公告)日：2023-12-21

    申请号：US18461709

    申请日：2023-09-06

    申请人： RTX CORPORATION

    发明人： Daniel Bernard Kupratis ,  Paul R. Hanrahan

    IPC分类号： F02K3/077 ,  F02K3/075

    CPC分类号： F02K3/077 ,  F02K3/075 ,  F02K1/72

    摘要： 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.

    Swirl preburner system and method
    5.
    发明授权
    Swirl preburner system and method 有权

    公开(公告)号：US11815049B2

    公开(公告)日：2023-11-14

    申请号：US17853025

    申请日：2022-06-29

    申请人： Stratolaunch, LLC

    发明人： Jeffery Tyler Thornburg

    IPC分类号： F02K9/52 ,  F02K3/075 ,  F02K9/48 ,  F02K9/64 ,  F23R3/20

    CPC分类号： F02K9/52 ,  F02K3/075 ,  F02K9/48 ,  F02K9/64 ,  F23R3/20

    摘要： A swirl preburner that includes a first core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end, the first swirl chamber comprising a first diameter at the first swirl chamber first end and a second smaller diameter at the first swirl chamber second end that is smaller than the first diameter; and a second core defining a second swirl chamber having a second swirl chamber first end and a second swirl chamber second end, the second swirl chamber comprising a third diameter at the second swirl chamber first end and a fourth smaller diameter at the second swirl chamber second end that is smaller than the third diameter, the first diameter being smaller than the third diameter and larger than the fourth smaller diameter.