Nacelle air intake and nacelle comprising such an air intake

Patent metadata

Field	Value
Publication number	US-11840352-B2
Application number	US-202117510643-A
Country	US
Kind code	B2
Filing date	Oct 26, 2021
Priority date	Apr 26, 2019
Publication date	Dec 12, 2023
Grant date	Dec 12, 2023

Abstract

An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.

First claim

What is claimed is:

1. An air intake for an aircraft engine nacelle, the air intake comprising:
a substantially cylindrical inner wall;
a substantially cylindrical outer wall;
a front lip connecting the substantially cylindrical inner wall and the substantially cylindrical outer wall;
a front mounting flange configured to cooperate with a rear flange of a wall of the aircraft engine forming a fan casing; and
a support structure configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the front mounting flange, in an assembled position,
wherein the substantially cylindrical outer wall comprises a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl, a portion of the substantially cylindrical outer wall being configured to bear at least against a support surface of the support structure, and
wherein the support structure is configured to be secured to the wall of the aircraft engine so that a load path, in the assembled position, passes directly from the substantially cylindrical outer wall towards the fan casing, while avoiding the substantially cylindrical inner wall.

2. The air intake according to claim 1 , wherein the front lip is integrated to the substantially cylindrical inner wall and/or the substantially cylindrical outer wall so as to form a wall in one-piece.

3. The air intake according to claim 1 , wherein the downstream end of the substantially cylindrical outer wall is located longitudinally at or upstream of the front mounting flange.

4. The air intake according to claim 3 , wherein the downstream end of the substantially cylindrical outer wall is located longitudinally upstream of the front mounting flange, at a distance less than 50% of a length of the air intake upstream relative to the front mounting flange.

5. The air intake according to claim 4 , wherein the downstream end of the outer wall is located longitudinally upstream of the front mounting flange at a distance between 10% and 20% of the length of the air intake upstream relative to the mounting flange.

6. The air intake according claim 1 , wherein the downstream end of the outer wall is located longitudinally downstream of the front mounting flange, and is configured to be located, in the assembled position, at a distance less than 50% of a length of the wall of the aircraft engine downstream relative to the mounting flange.

7. The air intake according claim 6 , wherein the downstream end of the substantially cylindrical outer wall is located longitudinally downstream of the front mounting flange at a distance less than 10% to 20% of the length of the wall of the aircraft engine downstream relative to the front mounting flange.

8. The air intake according to claim 1 , wherein the portion of the substantially cylindrical outer wall configured to bear at least against the support surface of the support structure comprises the downstream end of the substantially cylindrical outer wall.

9. The air intake according to claim 1 , wherein the substantially cylindrical outer wall is fastened to the support surface of the support structure by fasteners.

10. The air intake according to claim 1 , wherein the downstream end of the substantially cylindrical outer wall is configured to support the front end of the fan external cowl in the junction area, in the assembled position, via fasteners.

11. The air intake according to claim 1 , wherein the support structure includes access apertures configured to be crossed by maintenance tools during operations of maintenance of the air intake.

12. The air intake according to claim 1 , wherein the support structure is disposed continuously around the wall of the aircraft engine of the fan casing and comprises a partition.

13. The air intake according to claim 1 , wherein the support structure is disposed discontinuously around the wall of the aircraft engine of the fan casing and comprises a set of support rods.

14. The air intake according to claim 1 , wherein the support structure configured to be secured to the wall of the aircraft engine comprises a lower end of the support structure configured to be secured to a rear face of the rear flange of the wall of the aircraft engine.

15. A nacelle for an aircraft engine comprising an air intake according to claim 1 .

Assignees

• Safran Nacelles

Inventors

• Ferrier Gina
• Boileau Patrick
• Caruel Pierre

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title

• B64D2033/0273

  for jet engines · CPC title