Process for using an air input of a turboreactor nacelle comprising an air input lip which comprises a portion which can be moved to promote a thrust inversion phase

Patent metadata

Field	Value
Publication number	US-12134983-B2
Application number	US-202017601043-A
Country	US
Kind code	B2
Filing date	Apr 8, 2020
Priority date	Apr 17, 2019
Publication date	Nov 5, 2024
Grant date	Nov 5, 2024

Abstract

A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.

First claim

The invention claimed is:

1. A method for operating an air intake of an aircraft turbojet engine nacelle extending along an axis X oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, the air intake circumferentially extending about axis X and comprising an internal wall pointing to axis X and configured to guide the internal air flow and the reverse air flow, and an external wall, opposite to the internal wall, and configured to guide an external air flow around an exterior of the nacelle, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity therebetween, the air intake lip comprising a first radial thickness and at least one fixed portion and at least one movable portion that is translationally movable between a first position and a second position, and wherein when the at least one movable portion of the air intake lip is in the first position the air intake lip has an aerodynamic profile that is configured to guide the internal air flow over the internal wall to promote a thrust phase, the method comprising:
a step of moving the at least one movable portion during a thrust reversal phase of said turbojet engine to promote reverse thrust by moving relative to the fixed portion to the second position so that the air intake lip comprises a second radial thickness when in the second position that is less than the first radial thickness,
wherein the first radial thickness and the second radial thickness are measured in a same plane transverse to axis X, and
wherein the at least one movable portion is rigid and is translationally mounted for translating in a downstream direction in moving to the second position.

2. The method according to claim 1 , wherein the air intake lip comprises a plurality of movable portions distributed at a circumference of the air intake about axis X.

3. The method according to claim 1 , wherein the air intake lip comprises a single movable portion circumferentially extending about axis X.

4. The method according to claim 1 , wherein the air intake comprises at least one controllable moving member, the at least one controllable moving member moving the at least one movable portion from the first position to the second position.

5. The method according to claim 1 , wherein said turbojet engine comprises a fan configured to provide reverse thrust.

6. An aircraft turbojet engine extending along an axis X oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, said turbojet engine comprising:
a fan comprising variable pitch vanes configured to provide reverse thrust,
a nacelle comprising an air intake circumferentially extending about axis X and comprising an internal wall pointing to axis X and configured to guide the internal air flow and the reverse air flow, and an external wall, opposite to the internal wall, configured to guide an external air flow around an exterior of the nacelle,
wherein the internal wall and the external wall are connected to each other by an air intake lip so as to form an annular cavity therebetween, the air intake lip comprising at least one fixed portion and at least one movable portion, the at least one movable portion being rigid and translationally mounted to move between:
a first position, in which the air intake lip has a first radial thickness and an aerodynamic profile that guides the internal air flow over the internal wall to promote thrust, and
a second position, in which the at least one movable portion is configured to translationally move in a downstream direction relative to the at least one fixed portion so that the air intake lip has a second radial thickness which is less than the first radial thickness, and

wherein the first radial thickness and the second radial thickness are measured in a same plane transverse to axis X.

7. The aircraft turbojet engine according to claim 6 , wherein the air intake comprises at least one controllable moving member configured to move the at least one movable portion from the first position to the second position.

Assignees

• Safran Aircraft Engines

Inventors

• Mincu Daniel-Ciprian
• Lallia Mathieu Patrick Jean-Louis
• Sirvin Nicolas Joseph
• Worotynska Jagoda Alina
• Dautreppe Frederic
• Binder Anthony
• Lebeault Eva Julie

Classifications

• F02K1/66

  using reversing fan blades · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• B64D2033/0266

  specially adapted for particular type of power plants · CPC title

• B64D33/02

  of combustion air intakes · CPC title