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    COMBUSTOR WITH DILUTION OPENINGS
    1.
    发明公开
    COMBUSTOR WITH DILUTION OPENINGS 审中-公开

    公开(公告)号：EP4431808A3

    公开(公告)日：2024-10-23

    申请号：EP24184714.4

    申请日：2022-03-01

    申请人： General Electric Company

    发明人： VUKANTI,, Perumallu ,  LAKSHMANAN, Varun ,  BUCARO, Michael ,  NAIK, Pradeep ,  VISE, Steven ,  BENJAMIN, Michael

    IPC分类号： F23R3/04 ,  F23R3/14 ,  F23R3/00 ,  F23R3/50

    摘要： A gas turbine engine (10) including a compressor section (12) and a combustion section (14) in serial flow arrangement along an engine centerline (21), the combustion section having an annular dome wall circumscribing the engine centerline; an annular combustor liner extending from the annular dome wall to define an annular combustion chamber in combination with the annular dome wall; first and second, concentrically arranged and radially spaced, annular dilution holes formed in the annular dome wall to define an annular space between the first and second annular dilution holes; and multiple fuel injectors circumferentially spaced about the annular space between the first and second annular dilution holes.

    COMBUSTOR WITH DILUTION OPENINGS
    5.
    发明公开
    COMBUSTOR WITH DILUTION OPENINGS 审中-公开

    公开(公告)号：EP4209714A1

    公开(公告)日：2023-07-12

    申请号：EP22159555.6

    申请日：2022-03-01

    申请人： General Electric Company

    发明人： VUKANTI, Perumallu ,  LAKSHMANAN, Varun ,  BUCARO, Michael ,  NAIK, Pradeep ,  VISE, Steven ,  BENJAMIN, Michael

    IPC分类号： F23R3/04 ,  F23R3/14 ,  F23R3/00

    摘要： A gas turbine engine (10) including a compressor section (12) and a combustion section (14) in serial flow arrangement along an engine centerline (21), the combustion section (14) having a combustor liner (82, 182, 282, 382, 482, 582), a dome wall (90, 190, 290, 390, 490, 590, 690, 790) coupled to the combustor liner (82, 182, 282, 382, 482, 582), and a dome inlet (96, 196, 496, 596, 696, 796) located in the dome wall (90, 190, 290, 390, 490, 590, 690, 790), a fuel injector (76) fluidly coupled to the dome inlet (96, 196, 496, 596, 696, 796), a combustion chamber (86) fluidly coupled to the fuel injector (76) and defined at least in part by the combustor liner (82, 182, 282, 382, 482, 582) and the dome wall (90, 190, 290, 390, 490, 590, 690, 790), and at least one set of dilution openings (92, 93, 94, 192a, 192b, 193a, 193b, 292, 392, 492a, 492b) located in the dome wall (90, 190, 290, 390, 490, 590, 690, 790) and fluidly coupled to the combustion chamber (86).

    BAUGRUPPE EINER GASTURBINE MIT BRENNKAMMERLUFTBYPASS
    8.
    发明公开
    BAUGRUPPE EINER GASTURBINE MIT BRENNKAMMERLUFTBYPASS 审中-公开

    公开(公告)号：EP3926238A1

    公开(公告)日：2021-12-22

    申请号：EP21180176.6

    申请日：2021-06-17

    申请人： MAN Energy Solutions SE

    发明人： Cosic, Bernhard ,  Genin, Franklin

    IPC分类号： F23R3/10 ,  F23R3/04

    摘要： Die Erfindung betrifft eine Baugruppe für eine Gasturbine mit einer Brennkammer (10), einem Drallkörper (30), einer in einem Innenraum (11) der Brennkammer (10) angeordneten Verbrennungszone (13) und einer Luftzuführung, über welche der Brennkammer (10) eine Luftströmung zuführbar ist, wobei in einem von der Luft durchströmbaren Übergangsbereich von der Luftzuführung zu dem Drallkörper (30) ein Plenum (22) ausgebildet ist und die Baugruppe angrenzend an das Plenum (22), den Drallkörper (30) und die Brennkammer (10) einen die Brennkammer (10) abschließenden Deckel (40) aufweist, wobei die Baugruppe einen Luftführungskanal (60) als Brennkammerluftbypass aufweist, welcher ausgebildet ist, einen Teil der in die Baugruppe durch die Luftzuführung strömenden Luftströmung von dem Plenum (22) durch den Deckel (40) und durch den Drallkörper (30) an der Verbrennungszone (13) vorbei in die Brennkammer (10) zu leiten, so dass die durch die Luftzuführung führende Luftströmung (S0) in eine durch den Drallkörper (30) in die Verbrennungszone (13) führende Hauptströmung (S1) und eine an der Verbrennungszone (13) vorbei führende Nebenströmung (S0) aufgeteilt wird.

    GAS TURBINE ENGINE DILUTION CHUTE GEOMETRY
    9.
    发明公开
    GAS TURBINE ENGINE DILUTION CHUTE GEOMETRY 审中-公开

    公开(公告)号：EP3865775A1

    公开(公告)日：2021-08-18

    申请号：EP21156869.6

    申请日：2021-02-12

    申请人： Raytheon Technologies Corporation

    发明人： BINEK, Lawrence A. ,  GUSTAFSON, Brendan T.

    IPC分类号： F23R3/34 ,  F23R3/04

    摘要： A combustor (108) for a gas turbine engine (100; 200) includes a combustor liner (100) and a dilution chute (114; 214) integral and conformal with the combustor liner (110) to provide an outlet into the combustor (108) for fuel, wherein the dilution chute (114; 214) has at least one wall (122; 222) with a tapered edge (118; 218) extending into an interior of the combustor (108).

    COMBUSTOR HEAT SHIELD AND METHOD OF COOLING SAME
    10.
    发明公开
    COMBUSTOR HEAT SHIELD AND METHOD OF COOLING SAME 审中-公开

    公开(公告)号：EP3783262A1

    公开(公告)日：2021-02-24

    申请号：EP20191789.5

    申请日：2020-08-19

    申请人： Raytheon Technologies Corporation

    发明人： ICHIHASHI, Fumitaka ,  SNYDER, Timothy S ,  LIENAU, Jeffrey J ,  SEN, Baris A

    IPC分类号： F23R3/00 ,  F23R3/04 ,  F23R3/10

    摘要： A combustor (50) for a gas turbine engine includes an annular shell (52; 54), an annular bulkhead (60) connected to the shell (52; 54), and a heat shield panel (74). The heat shield panel (74) has a first surface (76) facing a combustion chamber (56) and a second surface (78) opposite the first surface (76). The heat shield panel (74) is mounted to the bulkhead (60) and defines a cooling chamber (98) between the bulkhead (60) and the heat shield panel (74). The heat shield panel (74) has a wall extending from the heat shield panel (74) toward the bulkhead (60) around at least a portion of a periphery of the heat shield panel (74). The wall includes a circumferential wall portion including at least one cooling air passage (136; 140) extending between the cooling chamber (98) and a cavity (132; 134) defined between the circumferential wall portion and the shell (52; 54). The at least one cooling air passage (136; 140)is configured to purge the cavity (132; 134) by directing a first cooling air stream (138; 142) from the cooling chamber (98) into the cavity (132; 134).