Assembly and method for handling an aircraft propulsion unit

Patent metadata

Field	Value
Publication number	US-12208994-B2
Application number	US-202117188520-A
Country	US
Kind code	B2
Filing date	Mar 1, 2021
Priority date	Aug 31, 2018
Publication date	Jan 28, 2025
Grant date	Jan 28, 2025

Abstract

A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.

First claim

What is claimed is:

1. A handling assembly for handling a propulsion unit including a nacelle and an aircraft turbojet engine, said handling assembly comprising:
a handling envelope covering at least a half-circumference of an outer wall of an air inlet of the nacelle, when said propulsion unit is mounted on said handling assembly;
at least two interfaces for fastening slings, said slings being configured to be connected to a hoisting system external to said handling assembly; and
an inflatable flexible element that, when inflated, comes into contact at least with an inner wall of the air inlet of the nacelle when the propulsion unit is mounted on said handling assembly.

2. The handling assembly according to claim 1 , wherein said handling envelope further includes at least two receiving pockets for receiving said at least two interfaces for fastening said slings, configured to hold said at least two interfaces for fastening said slings in position on said handling envelope.

3. The handling assembly according to claim 2 , wherein one interface of the at least two interfaces for fastening said slings includes:
a plate, shaped to be inserted into one receiving pocket of the at least two receiving pocket; and
a sling fastening fitting configured to receive one sling of said slings, the sling fastening fitting being secured to said plate.

4. The handling assembly according to claim 2 , wherein the at least two receiving pockets for receiving said at least two interfaces for fastening said slings are positioned on either side of a longitudinal plane of the handling assembly.

5. The handling assembly according to claim 1 , wherein said handling envelope includes a lateral extension shaped to at least partially cover a circumference of a downstream edge of the air inlet of the nacelle when the propulsion unit is mounted on the handling assembly.

6. The handling assembly according to claim 1 , wherein the inflatable flexible element, when inflated, occupies an entire inner space defined by the inner wall of the air inlet of the nacelle when the propulsion unit is mounted on said handling assembly.

7. The handling assembly according to claim 1 , wherein the inflatable flexible element includes an upstream protuberance coming into contact with a leading edge of the air inlet of the nacelle when said inflatable flexible element is inflated and when the propulsion unit is mounted on said handling assembly.

8. The handling assembly according to claim 1 , further comprising main fastening straps, a first end of each of the main fastening straps being attached to the inflatable flexible element and a second end of each of the main fastening straps being attached to said handling envelope.

9. The handling assembly according to claim 1 , further comprising a circumferential master strap, positioned on a flange for fastening the air inlet of the nacelle upstream of a fan casing of the aircraft turbojet engine.

10. The handling assembly according to claim 9 , further comprising fastening straps, a first end of each of the fastening straps being attached to the circumferential master strap and a second end of each of the fastening straps being attached to said handling envelope.

11. A method for handling a propulsion unit, said propulsion unit comprising a nacelle comprising an air inlet and an aircraft turbojet engine, including a fan casing, on which said air inlet of said nacelle is attached, said method comprising:
covering at least a half-circumference of an outer wall of the air inlet of the nacelle with the handling envelope of the handling assembly according to claim 1 ;
positioning the at least two interfaces of the handling assembly according to claim 1 for fastening slings on the handling envelope;
connecting the at least two interfaces for fastening said slings to a hoisting system external to said handling assembly by said slings; and
detaching said air inlet from the fan casing of the aircraft turbojet engine.

12. The handling method according to claim 11 , further comprising inflating the inflatable flexible element of the handling assembly inside an inner space defined by an inner wall of the air inlet of the nacelle until said inflatable flexible element comes into contact at least with the inner wall of the air inlet of the nacelle prior to covering at least the half-circumference of the outer wall of the air inlet of the nacelle with the handling envelope.

13. The handling method according to claim 12 , further comprising securing the handling assembly by attaching a first end of each one of main fastening straps to the inflatable flexible element and a second end of each one of said main fastening straps to the handling envelope after detaching the air inlet from the fan casing of the aircraft turbojet engine.

14. The handling method according to claim 13 , further comprising installing a circumferential master strap on a fastening flange of the air inlet of the nacelle upstream of the fan casing of the aircraft turbojet engine and attaching said master strap to the inflatable flexible element of the handling envelope by fastening straps prior to detaching the air inlet from the fan casing of the aircraft turbojet engine.

15. A method for handling a propulsion unit, said propulsion unit comprising a nacelle comprising an air inlet and an aircraft turbojet engine, including a fan casing, on which said air inlet of said nacelle is attached, said method comprising:
covering at least a half-circumference of an outer wall of the air inlet of the nacelle with a handling envelope of a handling assembly, wherein the handling assembly comprises the handling envelope covering at least the half-circumference of the outer wall of the air inlet of the nacelle, when said propulsion unit is mounted on said handling assembly, and at least two interfaces for fastening slings, said slings being configured to be connected to a hoisting system external to said handling assembly;
positioning the at least two interfaces of the handling assembly for fastening the slings on the handling envelope;
connecting the at least two interfaces for fastening said slings to the hoisting system external to said handling assembly by said slings;
inflating an inflatable flexible element of the handling assembly inside an inner space defined by the inner wall of the air inlet of the nacelle until said inflatable flexible element comes into contact at least with the inner wall of the air inlet of the nacelle prior to covering at least the half-circumference of the outer wall of the air inlet of the nacelle with the handling envelope; and
detaching said air inlet from the fan casing of the aircraft turbojet engine.

Assignees

• Safran Nacelles

Inventors

• Boileau Patrick

Classifications

• B64F5/50 Primary

  Handling or transporting aircraft components · CPC title

• B64D2033/0273

  for jet engines · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title