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公开(公告)号:US11512643B2
公开(公告)日:2022-11-29
申请号:US16876776
申请日:2020-05-18
申请人: Safran Nacelles
IPC分类号: F02C7/24 , B64D29/00 , B64C7/02 , B64C1/40 , F02K1/82 , B64D29/06 , F16B11/00 , F16L59/02 , F02C7/045
摘要: A device for securing at least one thermal protection mat to an internal fixed structure of a nacelle includes at least one removable fastening element for securing the at least one thermal protection mat to the internal fixed structure designed to be arranged between the mat and the internal fixed structure. The device includes at least one gripping element connected to the removable fastening element to project relative to the mat on the opposite side to the internal fixed structure, the removable fastening element being intended to be detached from the internal fixed structure by a pulling force exerted on the gripping element.
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2.
公开(公告)号:US10001064B2
公开(公告)日:2018-06-19
申请号:US15495413
申请日:2017-04-24
申请人: SAFRAN NACELLES
发明人: François Bellet , Cédric Renault
CPC分类号: F02C7/24 , F02K1/822 , F05D2220/323 , F05D2260/231 , F05D2260/30 , Y02T50/675
摘要: The present disclosure relates to an assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection, said structure including an inner face, on which the thermal protection is added, and an outer face constituting a portion of the inner surface of a cold flow path, the assembly including at least one channel put in fluid communication the inner face and the outer face of the structure.
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公开(公告)号:US20230029052A1
公开(公告)日:2023-01-26
申请号:US17862806
申请日:2022-07-12
申请人: SAFRAN NACELLES
摘要: A connecting rod for a nacelle of a turbine engine is described. The connecting rod includes a region configured to move the center of aerodynamic forces able to be exerted on the connecting rod, in the direction of an air flow intended to be generated during a thrust generated by the turbine engine.
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公开(公告)号:US09963999B2
公开(公告)日:2018-05-08
申请号:US15386954
申请日:2016-12-21
申请人: SAFRAN NACELLES
摘要: The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channeling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.
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