公开(公告)号：US20230088298A1

公开(公告)日：2023-03-23

申请号：US17904572

申请日：2021-02-16

Applicant: SAFRAN NACELLES

Inventor： Xavier CAZUC ,  Vincent Jean-Francois PEYRON ,  Jean-Philippe JORET ,  Sebastien Laurent Marie PASCAL

IPC: F02K1/72

Abstract: The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading (605) upstream of the cascade from a covering area (606) between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.

公开(公告)号：US20230059782A1

公开(公告)日：2023-02-23

申请号：US17797528

申请日：2021-02-05

Applicant: SAFRAN NACELLES

Inventor： Xavier CAZUC ,  Jean-Phillipe JORET

IPC: F02K1/72 ,  F02K1/76

Abstract: A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.

公开(公告)号：US20230184195A1

公开(公告)日：2023-06-15

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

IPC: F02K1/72 ,  F02K3/06

CPC classification number: F02K1/72 ,  F02K3/06

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：US20220316427A1

公开(公告)日：2022-10-06

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

IPC: F02K1/76

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.