公开(公告)号：US20230184193A1

公开(公告)日：2023-06-15

申请号：US18065875

申请日：2022-12-14

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Jérémie Rabineau ,  Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: F02K1/62 ,  F02K1/58

CPC classification number: F02K1/62 ,  F02K1/58 ,  F05D2220/323

Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

公开(公告)号：US11866178B2

公开(公告)日：2024-01-09

申请号：US17630869

申请日：2020-08-11

Applicant: SAFRAN NACELLES

Inventor： Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: B64D15/04 ,  B64D33/02

CPC classification number: B64D15/04 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.

公开(公告)号：US12258924B2

公开(公告)日：2025-03-25

申请号：US18065875

申请日：2022-12-14

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Jérémie Rabineau ,  Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: F02K1/62 ,  F02K1/58

Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

公开(公告)号：US20220267019A1

公开(公告)日：2022-08-25

申请号：US17630869

申请日：2020-08-11

Applicant: SAFRAN NACELLES

Inventor： Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: B64D33/02

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.