Thrust reverser at the door of a nacelle of a turbojet engine of an aircraft with a system for diverting fluids to the exterior

Patent metadata

Field	Value
Publication number	US-2023184193-A1
Application number	US-202218065875-A
Country	US
Kind code	A1
Filing date	Dec 14, 2022
Priority date	Dec 15, 2021
Publication date	Jun 15, 2023
Grant date	—

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.

First claim

1 . A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis, comprising:
a fixed structure and at least one door rotatable between a closed position in which said door provides aerodynamic continuity with the fixed structure for the circulation of an air flow and an open position in which the circulating air flow is diverted to the exterior and upstream of the thrust reverser, the fixed structure comprising a downstream frame comprising an upstream end spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis; at least one fluid diverter system for diverting fluids to the exterior of the thrust reverser associated with the door, wherein the fluid diverter system comprises at least one deflector group comprising at least one projection fixed onto one of the door or the fixed structure and extending locally from one of downstream end edge of the door or the upstream end of the downstream frame in the axial clearance and towards one of the upstream end of the downstream frame or the downstream end edge of the door, while leaving an axial gap between a free end of said projection and one of the upstream end of the downstream frame of the fixed structure or the downstream end edge of the door.

2 . The thrust reverser according to claim 1 , wherein the at least one projection includes at least one first projection fixed to the downstream end edge of the door and extending locally into the axial clearance and towards the upstream end of the downstream frame of the fixed structure and at least one second projection fixed to the upstream end of the downstream frame of the fixed structure and extending locally into the axial clearance and towards the downstream end edge of the door.

3 . The thrust reverser according to claim 2 , wherein the at least one first projection and the at least one second projection are in local direct radial and/or circumferential contact with one another.

4 . The thrust reverser according to claim 3 , wherein one of the at least one first projection or at least one the second projection is made from an elastic material capable of being deformed elastically on application of external stress and being restored to its initial form once the external stress has stopped.

5 . The thrust reverser according to claim 4 , wherein one of the at least one first projection or at least one the second projection is a seal made from a material that is more flexible than the other one of the at least one second projection or the at least one first projection.

6 . The thrust reverser according to claim 2 , wherein the at least one first projection and the at least one second projection are spaced apart circumferentially from one another by a circumferential clearance.

7 . The thrust reverser according to claim 6 , wherein the at least one first projection comprises an attachment portion fixed to the downstream end edge of the door and a diverting portion extending from an outer surface of the attachment portion to the exterior.

8 . The thrust reverser according to claim 6 , wherein the at least one second projection comprises an attachment portion fixed to the upstream end of the downstream frame of the fixed structure and a diverting portion extending from an outer surface of the attachment portion to the exterior.

9 . The thrust reverser according to claim 2 , wherein the number of first projections is greater than or equal to two and a number of second projections is greater than or equal to two, the number of first projections being different from the number of second projections.

10 . The thrust reverser according to claim 1 , wherein the at least one deflector group of the fluid diverter system comprises at least two deflector groups circumferentially spaced apart from each other.

11 . The thrust reverser according to claim 2 wherein the at least one fluid diverter system includes a first fluid diverter system comprising at least one first deflector group comprising the first projection and the second projection spaced apart circumferentially from the first projection by a circumferential clearance and a second fluid diverter system comprising at least one second deflector group comprising the first projection and the second projection in local direct radial and/or circumferential contact with the first projection.

12 . A nacelle of a turbojet engine of an aircraft comprising a thrust reverser with a door according to claim 1 .

Assignees

• Safran Nacelles

Inventors

• Joret Jean-Philippe
• Rabineau Jérémie
• Loncle Alexis Yves-Marie
• Valleroy Laurent Georges

Classifications

• F02K1/62 Primary

  by blocking the rearward discharge by means of flaps · CPC title

• F02K1/60 Primary

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/70

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F02K1/58

  Reversers mounted on the inner cone or the nozzle housing {or the fuselage} · CPC title