Propulsion assembly for an aircraft, comprising a load support

Patent metadata

Field	Value
Publication number	US-11565822-B2
Application number	US-201916708760-A
Country	US
Kind code	B2
Filing date	Dec 10, 2019
Priority date	Dec 12, 2018
Publication date	Jan 31, 2023
Grant date	Jan 31, 2023

Abstract

A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, said propulsion assembly comprising:
a pylon configured to be fastened below a wing of the aircraft,
a turbomachine comprising an engine attached to the pylon and a fan that is enclosed by a fan casing and is disposed upstream of the engine, said turbomachine having a longitudinal direction and a median plane,
a nacelle surrounding the engine and the fan casing and having a load support disposed in a top part of the nacelle and lateral cowls mounted in a hinged manner on either side of the load support,
a front fan attachment fastened between the fan casing and the load support, and
a rear pylon attachment fastened between the pylon and the load support,
wherein the front fan attachment comprises a positioning assembly disposed on the median plane, and two rotational systems disposed on either side of the median plane and of the positioning assembly,
wherein the positioning assembly comprises a base that is secured to the top part of the fan casing and a peg that is secured to the load support, extends vertically and is inserted into a bore in the base,
wherein each rotational system fastens the fan casing to the load support and allows rotation about an axis generally parallel to the longitudinal direction
wherein the rear pylon attachment comprises a first clevis fastened below the load support, a second clevis fastened above the pylon, and a double plate disposed in the first clevis and the second clevis,
wherein the double plate is mounted in a hinged manner on the first clevis about a first axis of rotation and on the second clevis about two second axes of rotation,
wherein the first axis of rotation is generally parallel to the longitudinal direction and included in the median plane,
wherein the two second axes of rotation are generally parallel to the longitudinal direction and disposed on either side of the median plane,
wherein the rear pylon attachment comprises two first clevises, each of which is fastened below the load support, a second clevis fastened above the pylon, and, for each first clevis, a link rod,
wherein each first clevis has a first axis of rotation generally parallel to the longitudinal direction and the two first axes of rotation are disposed on either side of the median plane,
wherein the second clevis has three second axes of rotation generally parallel to the longitudinal direction, one of which is central and included in the median plane and two others of which are lateral and disposed on either side of the median plane,
wherein one of the link rods is mounted in a hinged manner on one of the first clevises about the corresponding first axis of rotation and on the second clevis about a central second axis of rotation and a lateral second axis of rotation, and
wherein the other link rod is mounted in a hinged manner on the other of the first clevises about the corresponding first axis of rotation and on the second clevis about the other lateral second axis of rotation.

2. An aircraft having at least one propulsion assembly according to claim 1 .

3. A propulsion assembly for an aircraft, said propulsion assembly comprising:
a pylon configured to be fastened below a wing of the aircraft,
a turbomachine comprising an engine attached to the pylon and a fan that is enclosed by a fan casing and is disposed upstream of the engine, said turbomachine having a longitudinal direction and a median plane,
a nacelle surrounding the engine and the fan casing and having a load support disposed in a top part of the nacelle and lateral cowls mounted in a hinged manner on either side of the load support,
a front fan attachment fastened between the fan casing and the load support, and
a rear pylon attachment fastened between the pylon and the load support,
wherein the front fan attachment comprises a first clevis fastened in the top part of the fan casing and has two first axes of rotation generally parallel to the longitudinal direction and disposed on either side of the median plane, for each first axis of rotation, a second clevis fastened to the load support and disposed on the outside with respect to said first axis of rotation, where each second clevis has a second axis of rotation generally parallel to the longitudinal direction and for each first axis of rotation, a link rod mounted in a hinged manner on the first clevis about said first axis of rotation and on the second clevis about a corresponding second axis of rotation,
wherein the front fan attachment has at least one finger that is fastened to the load support and extends radially with respect to the longitudinal direction, and a groove that is coaxial with the longitudinal direction and realized at a perimeter of the fan casing, and wherein a free end of each finger sits in said groove.

Assignees

• Airbus Operations Sas

Inventors

• Auge Philippe
• Orteu Benoit
• Bernat Julien
• Geliot Jean
• Jalbert Delphine
• Ridray Frédéric
• Lafont Laurent
• Gardes Pascal

Classifications

• B64D2027/268

  Operations & Transport · mapped topic

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F02K3/06

  with front fan · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title