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公开(公告)号：US12110841B2
公开(公告)日：2024-10-08
申请号：US17652054
申请日：2022-02-22
发明人： Junichi Akatsuka
CPC分类号： F02K1/44 , B64C5/02 , B64C30/00 , B64D33/06 , F02K1/12 , F02K1/42 , F02K1/46 , F05D2220/80 , F05D2260/96
摘要： Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.
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公开(公告)号：US12031445B2
公开(公告)日：2024-07-09
申请号：US17688419
申请日：2022-03-07
申请人： Rohr, Inc.
发明人： Ann Khidekel
CPC分类号： F01D17/141 , F01D17/24 , F02K1/1207 , F02K1/805 , F02K1/11 , F02K1/12
摘要： An apparatus is provided for an aircraft propulsion system. This apparatus includes a variable area nozzle apparatus. The variable area nozzle apparatus includes a plurality of panels, a plurality of inter-panel members and an actuation system. The panels are arranged circumferentially about an axial centerline. The panels include a first panel and a second panel. The inter-panel members are arranged circumferentially about the axial centerline. The inter-panel members include a first inter-panel member between and connected to the first panel and the second panel. The first inter-panel member is configured from or otherwise includes an elastomeric material. The actuation system is configured to move the panels and the inter-panel members between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system includes a first linkage and a second linkage. The first linkage is coupled to the first panel. The second linkage is coupled to the second panel.
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公开(公告)号：US12018628B2
公开(公告)日：2024-06-25
申请号：US18252079
申请日：2021-11-05
CPC分类号： F02K1/1223 , F02K1/06 , F05D2250/37 , F05D2250/90 , F05D2260/50
摘要： A rear part for a turbojet engine includes a variable-geometry nozzle in which a convergent flap is provided with a lever supporting a bearing roller arranged axially between an upstream bearing wall and a downstream bearing wall, which are rigidly secured to a movable part capable of moving axially on command with respect to an upstream stator structure in such a way that the bearing roller is free to move with respect to the upstream and downstream bearing walls in a radial direction. During a downstream movement of the movable part, the upstream bearing wall pushes the lever to pivot a downstream end of the convergent flap towards the longitudinal axis. Operation of the drive mechanism for moving the movable part can thus be optimized while limiting the size and the mass of the mechanism for controlling the flaps.
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公开(公告)号：US20240092495A1
公开(公告)日：2024-03-21
申请号：US18368922
申请日：2023-09-15
申请人： Rohr, Inc.
发明人： Imad D. Ghandour , Timothy Gormley
摘要： An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.
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公开(公告)号：US11867136B2
公开(公告)日：2024-01-09
申请号：US17554874
申请日：2021-12-17
申请人： Rohr, Inc.
发明人： Timothy Gormley
CPC分类号： F02K1/1215 , F02K1/36 , F02K1/62 , F05D2240/128 , F05D2260/50 , F05D2260/601
摘要： A variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. A nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions and respective open positions. A translating ejector sleeve is mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position and a second axial position.
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公开(公告)号：US20240003316A1
公开(公告)日：2024-01-04
申请号：US18252079
申请日：2021-11-05
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F05D2250/37 , F05D2250/90 , F05D2260/50
摘要： A rear part for a turbojet engine includes a variable-geometry nozzle in which a convergent flap is provided with a lever supporting a bearing roller arranged axially between an upstream bearing wall and a downstream bearing wall, which are rigidly secured to a movable part capable of moving axially on command with respect to an upstream stator structure in such a way that the bearing roller is free to move with respect to the upstream and downstream bearing walls in a radial direction. During a downstream movement of the movable part, the upstream bearing wall pushes the lever to pivot a downstream end of the convergent flap towards the longitudinal axis. Operation of the drive mechanism for moving the movable part can thus be optimized while limiting the size and the mass of the mechanism for controlling the flaps.
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公开(公告)号：US11772809B2
公开(公告)日：2023-10-03
申请号：US17535995
申请日：2021-11-27
CPC分类号： B64D33/04 , B64C1/16 , B64D27/20 , B64D29/04 , F02K1/002 , F02K1/006 , F02K1/1223 , F02K1/80
摘要： A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.
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公开(公告)号：US11725608B2
公开(公告)日：2023-08-15
申请号：US17734723
申请日：2022-05-02
申请人： Rohr, Inc.
发明人： Steve A. Wylie
IPC分类号： F02K1/12
CPC分类号： F02K1/1207 , F05D2220/323
摘要： An aircraft system includes a propulsion system structure, a variable area nozzle and a linkage system. The propulsion system structure is moveable between a first position and a second position. The variable area nozzle is fluidly coupled with a duct in the propulsion system structure. The variable area nozzle is moveable between a first configuration and a second configuration. An exit area of the variable area nozzle has a first value when the variable area nozzle is in the first configuration and a second value when the variable area nozzle is in the second configuration. The variable area nozzle includes a flap moveably connected to the propulsion system structure. The linkage system mechanically links the variable area nozzle with the propulsion system structure. The linkage system includes a driver linkage, a first bell crank, a bridge linkage, a second bell crank, a follower linkage and a crank arm.
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公开(公告)号：US20230213003A1
公开(公告)日：2023-07-06
申请号：US17567385
申请日：2022-01-03
CPC分类号： F02K1/805 , F02K1/12 , F16J15/3436
摘要： In some embodiments, apparatuses are provided herein useful to sealing a gap, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal that includes a plunger, a retaining element, a guide pin, and a biasing element. The plunger includes a sealing edge and an actuating edge having at least one recess and an opening formed therein. The biasing element and a portion of the guide pin are nested in the recess. The retaining element anchor the plunger to the retaining element. The retaining element also anchors the plunger seal to the housing When installed in a gap, the housing engages the flap and the plunger engages the sidewall. The biasing element is under compression and urges the guide pin into the actuating edge to urge the plunger toward the sidewall and seal the gap.
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公开(公告)号：US20230160355A1
公开(公告)日：2023-05-25
申请号：US17532673
申请日：2021-11-22
申请人： ROHR, INC.
CPC分类号： F02K1/70 , F02K1/763 , F02K1/1223 , F05D2220/323 , F05D2240/128 , F05D2260/57 , F05D2260/605
摘要： An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.
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