公开(公告)号：US20230046876A1

公开(公告)日：2023-02-16

申请号：US17758037

申请日：2020-12-18

Applicant: SAFRAN NACELLES

Inventor： Sebastien Laurent Marie PASCAL ,  Laurent Georges VALLEROY ,  Paul FERREY

IPC: F02K1/32

Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.

公开(公告)号：US20230039569A1

公开(公告)日：2023-02-09

申请号：US17790684

申请日：2020-12-18

Applicant: SAFRAN NACELLES

Inventor： Sebastien Laurent Marie PASCAL ,  Patrick GONIDEC ,  Alexandre PHI ,  Paul FERREY

IPC: F02K1/62 ,  B64D29/04

Abstract: A thrust reverser including doors and at least one flexible deflector obstructing a lateral opening of the thrust reverser when the doors are open. Such a deflector allows better controlling the airflows in thrust reverser configuration and maximizing the counter-thrust force.

公开(公告)号：US20230067232A1

公开(公告)日：2023-03-02

申请号：US17790661

申请日：2020-12-18

Applicant: SAFRAN NACELLES

Inventor： Sebastien Laurent Marie PASCAL

IPC: F02K1/62

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.

公开(公告)号：US20240209813A1

公开(公告)日：2024-06-27

申请号：US18556312

申请日：2022-04-27

Applicant: SAFRAN NACELLES

Inventor： Sebastien Laurent Marie PASCAL ,  Luigi BISANTI

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/763

Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle, this thrust reverser having a generally annular shape around an axis and including in particular flaps for deflecting the secondary flow through gratings, each of these flaps having a rigid wall and sealing elements located on the outer face of this wall, these sealing elements extending along side edges of the flap so as to provide a seal along these edges in the first position.

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.