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公开(公告)号：US11286880B2
公开(公告)日：2022-03-29
申请号：US16394128
申请日：2019-04-25
申请人： Safran Nacelles
发明人： Pierre Caruel , Regis Giard , Denis Guillois , Philippe Vancon
摘要： A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.
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公开(公告)号：US11939933B2
公开(公告)日：2024-03-26
申请号：US17596525
申请日：2020-06-09
摘要： In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.
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公开(公告)号：US11685538B2
公开(公告)日：2023-06-27
申请号：US16587887
申请日：2019-09-30
申请人： Safran Nacelles
发明人： Denis Guillois
CPC分类号： B64D27/26 , B64D27/20 , B64D29/04 , B64D29/06 , B64D2027/262
摘要： An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.
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公开(公告)号：US12129042B2
公开(公告)日：2024-10-29
申请号：US18292765
申请日：2022-07-22
申请人： SAFRAN NACELLES
发明人： Denis Guillois , Loïc Chapelain , Marc Versaevel
CPC分类号： B64D33/02 , B64D2033/0206 , F02C7/24 , F05D2260/96
摘要： An acoustic assembly including a multicellular acoustic panel having at least one through cavity along a direction X, wherein the acoustic assembly further includes at least one sealing element including a body enclosing one or more acoustic cells, the body being able to be inserted into the cavity and extending along the direction X between a first face and a second face, the sealing element further including a seal on the second face of the body able to ensure the sealing with the acoustic panel.
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公开(公告)号：US12116931B2
公开(公告)日：2024-10-15
申请号：US17510785
申请日：2021-10-26
申请人： Safran Nacelles
IPC分类号： F02C7/045
CPC分类号： F02C7/045 , F05D2220/32 , F05D2230/20 , F05D2230/60
摘要： An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.
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公开(公告)号：US11486332B2
公开(公告)日：2022-11-01
申请号：US16446683
申请日：2019-06-20
申请人： Safran Nacelles
发明人： Denis Guillois
摘要： A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.
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