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    VARIABLE AREA NOZZLE ASSEMBLY
    1.
    发明公开
    VARIABLE AREA NOZZLE ASSEMBLY 审中-公开

    公开(公告)号：EP4242445A1

    公开(公告)日：2023-09-13

    申请号：EP23160603.9

    申请日：2023-03-07

    申请人： Rohr, Inc.

    发明人： GORMLEY, Timothy

    IPC分类号： F02K1/12 ,  F02K1/15

    摘要： A variable area nozzle assembly (46) for a gas turbine engine includes a fixed structure (48) surrounding an exhaust duct (50) extending along a nozzle centerline (52). The fixed structure (48) includes an upper side and a lower side opposite the upper side (58). The variable area nozzle assembly (46) further includes a nozzle disposed about the nozzle centerline (52). The nozzle (54) includes a nozzle throat cross-sectional area and a nozzle outlet cross-sectional area downstream of the nozzle throat cross-sectional area. The nozzle includes an upper panel (74) and a lower panel (76). The upper panel (74) includes an upper downstream end (80) and the lower panel (76) including a lower downstream end (80). The upper downstream end (80) and the lower downstream end (80) define a portion of the nozzle throat cross-sectional area (86). The variable area nozzle assembly (46) further includes a nozzle actuation system (130) including an upper shaft (144) connected to the upper panel (76) and a lower shaft (162) connected to the lower panel (76).

    THRUST REVERSER FOR VARIABLE AREA NOZZLE
    2.
    发明公开
    THRUST REVERSER FOR VARIABLE AREA NOZZLE 审中-公开

    公开(公告)号：EP4242444A1

    公开(公告)日：2023-09-13

    申请号：EP23160595.7

    申请日：2023-03-07

    申请人： Rohr, Inc.

    发明人： GORMLEY, Timothy

    IPC分类号： F02K1/12 ,  F02K1/00 ,  F02K1/62

    摘要： A variable area nozzle assembly (46) for a gas turbine engine includes a fixed structure (48) surrounding an exhaust duct extending along a nozzle centerline. The fixed structure (48) further includes a first lateral side (62) and a second lateral side (64) opposite the first lateral side (62). The variable area nozzle assembly (46) further includes a nozzle (54). The nozzle (54) includes a nozzle outlet (119) including a nozzle outlet cross-sectional area. The variable area nozzle assembly (46) further includes a thrust reverser system (132) including a first thrust reverser door (134) and a second thrust reverser door (136). The first thrust reverser door (134) is pivotably mounted to the fixed structure (48) at the first lateral side (62). The second thrust reverser door (136) is pivotably mounted to the fixed structure (48) at the second lateral side (64). The first thrust reverser door (134) and the second thrust reverser door (136) define a portion of the nozzle outlet (119) of the nozzle.

    VARIABLE AREA NOZZLE FOR AIRCRAFT PROPULSION SYSTEM
    3.
    发明公开
    VARIABLE AREA NOZZLE FOR AIRCRAFT PROPULSION SYSTEM 审中-公开

    公开(公告)号：EP4242443A1

    公开(公告)日：2023-09-13

    申请号：EP23160551.0

    申请日：2023-03-07

    申请人： Rohr, Inc.

    发明人： KHIDEKEL, Ann

    IPC分类号： F02K1/12

    摘要： An apparatus for an aircraft propulsion system includes a variable area nozzle apparatus (66). The variable area nozzle apparatus (66) includes a plurality of panels (76), a plurality of inter-panel members (78) and an actuation system (74). The panels (76) are arranged circumferentially about an axial centerline (32). The panels (76) include a first panel (76A) and a second panel (76B). The inter-panel members (78) are arranged circumferentially about the axial centerline (32). The inter-panel members (78) include a first inter-panel member (78) between and connected to the first panel (76A) and the second panel (76B). The first inter-panel member (78) is configured from or otherwise includes an elastomeric material. The actuation system (74) is configured to move the panels (76) and the inter-panel members (78) between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system (74) includes a first linkage (110) and a second linkage (110). The first linkage (110) is coupled to the first panel (76A). The second linkage (110) is coupled to the second panel (76B).