-
公开(公告)号：US11655760B2
公开(公告)日：2023-05-23
申请号：US17427565
申请日：2020-02-05
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.
-
Patent Agency Ranking
公开(公告)号：US11608781B2
公开(公告)日：2023-03-21
申请号：US17427563
申请日：2020-01-22
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.
-
公开(公告)号：US11591960B2
公开(公告)日：2023-02-28
申请号：US17427548
申请日：2020-01-22
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.
-
公开(公告)号：US12049853B2
公开(公告)日：2024-07-30
申请号：US17999106
申请日：2021-05-17
Applicant: SAFRAN NACELLES
Inventor： Xavier Cazuc , Jean-Philippe Joret , Vincent Jean-François Peyron , Sébastien Laurent Marie Pascal
Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.
-
公开(公告)号：US11987372B2
公开(公告)日：2024-05-21
申请号：US17616422
申请日：2020-06-02
Applicant: SAFRAN NACELLES
Abstract: An assembly including a nacelle element, such as a cover, a device for locking the nacelle element, a key for locking/unlocking the locking device and an indicator for indicating the position of the locking device. This assembly includes a control device which is configured to be actuated by the key when the key is withdrawn from the locking device so as to make the indicator move from a first state to a second state, the state of the indicator being representative of the locked or unlocked position of the locking device.
-
公开(公告)号：US11952963B2
公开(公告)日：2024-04-09
申请号：US17843219
申请日：2022-06-17
Applicant: Safran Nacelles
Inventor： Xavier Cazuc , Vincent Dutot , Sébastien Laurent Marie Pascal , Stephane Riquier , Patrick André Boileau , Fabien Jourdan
Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.
-
-
-
-
-
Search Results
6
records
(took 0.069 seconds)
