Turbojet engine comprising a nacelle with an air intake to promote a reversed thrust phase

Patent metadata

Field	Value
Publication number	US-11933246-B2
Application number	US-202017600071-A
Country	US
Kind code	B2
Filing date	Apr 8, 2020
Priority date	Apr 17, 2019
Publication date	Mar 19, 2024
Grant date	Mar 19, 2024

Abstract

An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.

First claim

The invention claimed is:

1. An aircraft turbojet engine extending along an axis X and 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 configured to provide reverse thrust;
a nacelle comprising an air intake, the air intake circumferentially extending about the axis X and comprising an internal wall pointing to the 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, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, wherein the air intake further comprising:
a deflection device comprising at least one deflection member movably mounted between an extended position, in which the at least one deflection member projectingly extends from the internal wall or from the air intake lip in a radially internal extension direction pointing to the axis X or in a longitudinal extension direction relative to the axis X in order to allow a separation of the reverse air flow from the internal wall to promote the thrust reversal phase, and a retracted position, in which the air intake has an aerodynamic profile so as to guide the internal air flow onto the internal wall to promote the thrust phase;

wherein the at least one deflection member is translationally mounted between the extended position and the retracted position; and
wherein the deflection device comprises a single deflection member circumferentially extending about the axis X.

2. The aircraft turbojet engine according to claim 1 , wherein the extension direction is oriented upstream.

3. The aircraft turbojet engine according to claim 1 , wherein the annular cavity extends along a longitudinal direction X 20 that substantially parallel to the axis X and the extension direction forms an extension angle with respect to the longitudinal direction X 20 that is between 90° and 140°.

4. The aircraft turbojet engine according to claim 1 , wherein the deflection device comprises at least one controllable active moving member configured to move the at least one deflection member from the retracted position to the extended position.

5. A method for operating the aircraft turbojet engine according to claim 1 , the method comprising, during a thrust reversal phase of said turbojet, a step of moving the at least deflection member into an extended position so that said at least one deflection member projectingly extends from the internal wall or from the air intake lip along a radially internal extension direction pointing to the axis X or a longitudinal extension direction relative to the axis X to separate the reverse air flow from the internal wall to promote the thrust reversal phase.

6. An aircraft turbojet engine extending along an axis X and 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 configured to provide reverse thrust;
a nacelle comprising an air intake, the air intake circumferentially extending about the axis X and comprising an internal wall pointing to the 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, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, wherein the air intake further comprising:
a deflection device comprising at least one deflection member movably mounted between an extended position, in which the at least one deflection member projectingly extends from the internal wall or from the air intake lip in a radially internal extension direction pointing to the axis X or in a longitudinal extension direction relative to the axis X in order to allow a separation of the reverse air flow from the internal wall to promote the thrust reversal phase, and a retracted position, in which the air intake has an aerodynamic profile so as to guide the internal air flow onto the internal wall to promote the thrust phase; and

wherein the deflection device comprises at least one passive moving member configured to move the at least one deflection member from the retracted position to the extended position by action of the reverse air flow.

7. The aircraft turbojet engine according to claim 6 , wherein the deflection device comprises a plurality of deflection members distributed at the air intake about the axis X.

8. The aircraft turbojet engine according to claim 6 , wherein the deflection device comprises at least one row comprising a plurality of deflection members positioned at a same radial distance from the axis X.

9. A method for operating the aircraft turbojet engine according to claim 6 , the method comprising, during a thrust reversal phase of said turbojet, a step of moving the at least deflection member into an extended position so that said at least one deflection member projectingly extends from the internal wall or from the air intake lip along a radially internal extension direction pointing to the axis X or a longitudinal extension direction relative to the axis X to separate the reverse air flow from the internal wall to promote the thrust reversal phase.

10. An aircraft turbojet engine extending along an axis X and 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 configured to provide reverse thrust;
a nacelle comprising an air intake, the air intake circumferentially extending about the axis X and comprising an internal wall pointing to the 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, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, wherein the air intake further comprising:
a deflection device comprising at least one deflection member movably mounted between an extended position, in which the at least one deflection member projectingly extends from the internal wall or from the air intake lip in a radially internal extension direction pointing to the axis X or in a longitudinal extension direction relative to the axis X in order to allow a separation of the reverse air flow from the internal wall to promote the thrust reversal phase, and a retracted position, in which the air intake has an aerodynamic profile so as to guide the internal air flow onto the internal wall to promote the thrust phase; and

wherein the deflection device comprises a cover member movably mounted between a covered position, in which said cover member covers the at least one deflection member in the retracted position so as to provide an aerodynamic profile, and an uncovered position, in which said cover member is offset from the covered position so as to bring the at least one deflection member to the extended position.

11. A method for operating the aircraft turbojet engine according to claim 10 , the method comprising, during a thrust reversal phase of said turbojet, a step of moving the at least deflection member into an extended position so that said at least one deflectio

Assignees

• Safran Aircraft Engines

Inventors

• Mincu Daniel-Ciprian
• LECORDIX JEAN-LOÏC HERVé
• Sirvin Nicolas Joseph
• Dautreppe Frédéric
• Binder Anthony
• Lebeault Eva Julie

Classifications

• F02K1/62 Primary

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

• B64C23/06 Primary

  by generating vortices · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title