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    CHAMBER FOR ROTATING DETONATION ENGINE AND WALL OBSTACLES FOR SAME
    2.
    发明申请
    CHAMBER FOR ROTATING DETONATION ENGINE AND WALL OBSTACLES FOR SAME 有权

    公开(公告)号：US20220325893A1

    公开(公告)日：2022-10-13

    申请号：US17670575

    申请日：2022-02-14

    Applicant: Raytheon Technologies Corporation

    Inventor： Christopher Britton Greene ,  Peter AT Cocks ,  Xiaoyi Li ,  James M. Donohue

    IPC: F23R3/56 ,  F23R3/12 ,  F23R3/50

    Abstract: A combustor for a rotating detonation engine includes an outer tapered wall extending along an axis; an inner tapered wall extending along the axis, wherein the inner tapered wall is positioned within the outer tapered wall to define an annular combustion chamber having an annular gap between the outer tapered wall and the inner tapered wall, wherein the outer tapered wall is moveable relative to the inner tapered wall along the axis, and wherein movement of the outer tapered wall relative to the inner tapered wall changes the annular gap of the annular combustion chamber. Obstacles can be positioned on either or both of inner and outer wall to enhance turbulence within the combustion chamber.

    Supercritical fluid systems
    5.
    发明授权
    Supercritical fluid systems 有权

    公开(公告)号：US11225905B1

    公开(公告)日：2022-01-18

    申请号：US17018471

    申请日：2020-09-11

    Applicant: Raytheon Technologies Corporation

    Inventor： Brian M. Holley ,  Christopher Britton Greene

    IPC: F02C1/10 ,  F01K25/10 ,  F01K7/32 ,  F01K21/04 ,  F02C7/18 ,  F02C6/18

    Abstract: Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine operably coupled to the compressor, a generator operably coupled to the turbine and configured to generate power, a primary working fluid flow path having a primary working fluid configured to pass through the compressor, a separator, the turbine, and back to the compressor, and a secondary working fluid flow path passing through the generator, the compressor, the separator, and back to the generator. The primary working fluid is supercritical carbon dioxide (sCO2) and the secondary working fluid is a fluid having at least one of a density less than the primary working fluid and a molecular size smaller than the primary working fluid.

    Supercritical fluid systems
    6.
    发明授权
    Supercritical fluid systems 有权

    公开(公告)号：US11624317B2

    公开(公告)日：2023-04-11

    申请号：US17559281

    申请日：2021-12-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Brian M. Holley ,  Christopher Britton Greene

    IPC: F02C1/10 ,  F01K25/10 ,  F01K7/32 ,  F01K21/04 ,  F02C7/18 ,  F02C6/18

    Abstract: Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine, and a generator. A primary working fluid flow path has a primary working fluid that passes through the compressor, a separator, the turbine, and back to the compressor. A secondary working fluid flow path having a secondary working fluid that passes through the generator, the compressor, the separator, and back to the generator. The primary working fluid and the secondary working fluid are compressed and mixed within the compressor to form a mixture of the two fluids and the separator separates the mixture of the two fluids to direct the primary working fluid back to the turbine and the secondary working fluid to the generator.

    REGENERATIVE COOLING AND ADJUSTABLE THROAT FOR ROTATING DETONATION ENGINE
    7.
    发明申请
    REGENERATIVE COOLING AND ADJUSTABLE THROAT FOR ROTATING DETONATION ENGINE 有权

    公开(公告)号：US20220333530A1

    公开(公告)日：2022-10-20

    申请号：US17231487

    申请日：2021-04-15

    Applicant: Raytheon Technologies Corporation

    Inventor： Christopher Britton Greene ,  James M. Donohue ,  Peter AT Cocks

    IPC: F02C7/224 ,  F23R3/44 ,  F23R3/32 ,  F23R3/56 ,  F02C7/264 ,  F02C3/24

    Abstract: A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.

    SUPERCRITICAL FLUID SYSTEMS
    8.
    发明申请
    SUPERCRITICAL FLUID SYSTEMS 有权

    公开(公告)号：US20220275752A1

    公开(公告)日：2022-09-01

    申请号：US17559281

    申请日：2021-12-22

    Applicant: Raytheon Technologies Corporation

    Inventor： Brian M. Holley ,  Christopher Britton Greene

    IPC: F02C1/10 ,  F01K25/10 ,  F01K7/32 ,  F01K21/04 ,  F02C7/18

    Abstract: Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine, and a generator. A primary working fluid flow path has a primary working fluid that passes through the compressor, a separator, the turbine, and back to the compressor. A secondary working fluid flow path having a secondary working fluid that passes through the generator, the compressor, the separator, and back to the generator. The primary working fluid and the secondary working fluid are compressed and mixed within the compressor to form a mixture of the two fluids and the separator separates the mixture of the two fluids to direct the primary working fluid back to the turbine and the secondary working fluid to the generator.

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