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    INLET ARRANGEMENT, A PROPULSION SYSTEM, AND AN AIRCRAFT
    4.
    发明公开
    INLET ARRANGEMENT, A PROPULSION SYSTEM, AND AN AIRCRAFT 审中-公开

    公开(公告)号：EP4223645A1

    公开(公告)日：2023-08-09

    申请号：EP23154851.2

    申请日：2023-02-03

    申请人： Gulfstream Aerospace Corporation

    发明人： FREUND, Donald ,  MUZYCHKA, Derek ,  KLUTZKE, Douglas

    IPC分类号： B64D33/02 ,  F02C7/042 ,  B64D27/14

    摘要： An inlet arrangement for a propulsion system includes an actuator (64), a linkage (62) and an inlet assembly (32, 3). The inlet assembly (32, 3) includes (1) a lip (2, 35, 40), (2) a cowl (42) extending downstream from the lip (2, 35, 40), the cowl (42) defining an external surface (72, 74) of the inlet assembly (32, 3), (3) an inlet duct (44) extending downstream from the lip (2, 35, 40), the inlet duct (44) disposed radially inward of the cowl (42), and (4) a movable component associated with the lip (2, 35, 40), the cowl (42), or the inlet duct (44). An outer surface (72) of the inlet duct (44) and an inner surface (74) of the cowl (42) define a gap (76) therebetween. The linkage (62) is disposed in the gap (76) and coupled with the moveable component. The linkage (62) is configured to move within the gap (76) and to move the moveable component when the linkage (62) moves. The actuator (64) is coupled with the linkage (62) and moves the linkage (62) when the actuator (64) is actuated. The actuator (64) is mounted remotely from the inlet assembly (32, 3).

    AIR INLET DEVICE FOR AN INLET DUCT TO AN ENGINE OF AN AIRCRAFT
    5.
    发明公开
    AIR INLET DEVICE FOR AN INLET DUCT TO AN ENGINE OF AN AIRCRAFT 审中-公开

    公开(公告)号：EP4180639A1

    公开(公告)日：2023-05-17

    申请号：EP21207683.0

    申请日：2021-11-11

    申请人： Airbus Defence and Space GmbH

    发明人： Stangl, Wolfgang

    IPC分类号： F01D17/16 ,  F02C7/042 ,  F04D29/56 ,  F02K1/82

    摘要： An air inlet device (100) for an air inlet of an aircraft is described. The air inlet device (100) has a plurality of air guide arrangements (130). An air guide arrangement (130) has an inlet plate (131), an outlet plate (139), and a plurality of pivot plates (133, 135, 137) arranged therebetween. The outlet plate and the pivot plates can be rotated about a central axis of the air inlet device by adjustment rings, so that the air guide arrangement (130) is transitioned from a linear state to a curved state, and vice versa. The air inlet device allows for selective switching between a state with low radar signature and a state with high performance of an engine.

    LOW NOISE AEROENGINE INLET SYSTEM
    10.
    发明公开
    LOW NOISE AEROENGINE INLET SYSTEM 审中-公开

    公开(公告)号：EP3792468A1

    公开(公告)日：2021-03-17

    申请号：EP20162380.8

    申请日：2015-08-19

    申请人： Pratt & Whitney Canada Corp.

    发明人： LABRECQUE, Michel ,  COUTURE-GAGNON, Vincent ,  ULLYOTT, Richard

    IPC分类号： F02C7/042 ,  F02C7/045

    摘要： An aeroengine has an inlet system (22) which includes a deformable wall (36,38) disposed adjacent a peripheral wall (32,34) of an inlet duct (24) and a plurality of acoustic cells (40) attached to a back side (42) in fluid communication through respective holes (41) in the deformable wall (36,38) with an inlet duct air flow (11). The deformable wall (36,38) selectively forms part of the peripheral wall (32,34) of the inlet duct (24) when in an undeployed position and selectively forms a curved profile projecting into the inlet duct (24) to reduce line-of-sight noise propagation through the inlet duct (24).