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公开(公告)号：US20240102655A1
公开(公告)日：2024-03-28
申请号：US18164491
申请日：2023-02-03
发明人： Justin M Locke , Dennis M Moura , Duane C McCormick , Scott A Liljenberg , Theodore R Strickland , William Proscia
CPC分类号： F23R3/28 , F23D11/38 , F23K5/06 , F23R3/06 , F23R3/12 , F23R3/14 , F23R3/346 , F23R3/50 , F23R2900/00014 , F23R2900/03042
摘要： A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
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公开(公告)号：US11719439B2
公开(公告)日：2023-08-08
申请号：US17380494
申请日：2021-07-20
发明人： Carey Clum , Dennis M Moura
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23M2900/05004 , F23R2900/00018 , F23R2900/03043 , F23R2900/03045
摘要： A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.
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