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    CAVITY STABILIZED DETONATION COMBUSTOR ASSEMBLY OF A ROTATING DETONATION ENGINE
    3.
    发明申请
    CAVITY STABILIZED DETONATION COMBUSTOR ASSEMBLY OF A ROTATING DETONATION ENGINE 审中-公开

    公开(公告)号：US20190086086A1

    公开(公告)日：2019-03-21

    申请号：US15711742

    申请日：2017-09-21

    Applicant: General Electric Company

    Inventor： Venkat Eswarlu Tangirala ,  Anthony Dean ,  Narendra Digamber Joshi ,  Sarah Monahan

    IPC: F23R3/04 ,  F23R7/00 ,  F02C5/04 ,  F02C3/16

    Abstract: A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.

    ROTATING DETONATION ENGINE INCLUDING SUPPLEMENTAL COMBUSTOR AND METHOD OF OPERATING SAME
    4.
    发明申请
    ROTATING DETONATION ENGINE INCLUDING SUPPLEMENTAL COMBUSTOR AND METHOD OF OPERATING SAME 审中-公开

    公开(公告)号：US20180179951A1

    公开(公告)日：2018-06-28

    申请号：US15390112

    申请日：2016-12-23

    Applicant: General Electric Company

    Inventor： Venkat Eswarlu Tangirala ,  Keith Robert McManus ,  Michael Bowman ,  Narendra Joshi ,  Joel Haynes ,  Anthony Dean

    IPC: F02C3/16 ,  F02C3/04 ,  F02C3/34

    CPC classification number: F02C3/16 ,  F02C3/34 ,  F02C5/02 ,  F23R2900/03341

    Abstract: A turbine engine includes at least one compressor configured to increase pressure of a fluid flow and a primary combustor coupled in flow communication with the at least one compressor. The primary combustor is configured to receive pressurized fluid flow from the at least one compressor. The primary combustor includes a housing defining at least one combustion chamber. The primary combustor is configured for a rotating detonation process to occur within said at least one combustion chamber. The turbine engine also includes at least one supplemental combustor coupled in flow communication with the primary combustor. The at least one supplemental combustor is configured to receive combustion products and perform a combustion operation. The turbine engine further includes a turbine assembly coupled in flow communication with the at least one supplemental combustor. The turbine assembly is configured to receive combustion products from the at least one supplemental combustor.

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