Propulsion assembly for an aircraft, comprising a load bearer

Patent metadata

Field	Value
Publication number	US-12344388-B2
Application number	US-202318119128-A
Country	US
Kind code	B2
Filing date	Mar 8, 2023
Priority date	Mar 8, 2022
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

A propulsion assembly is disclosed including a pylon, a turbomachine having an engine and a fan surrounded by a fan casing, a nacelle surrounding the engine and the fan casing, and including a load bearer positioned at the upper part of the nacelle, a forward fan mount between a frontal zone of the fan casing and a frontal zone of the load bearer, a rear pylon mount between the pylon and the load bearer, and a positioning assembly providing positioning between the fan casing and the load bearer. The propulsion assembly is configured to control the separations between the cowls mounted in a moveable manner on the load bearer and a nose cowl.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, comprising:
a pylon configured to be fastened beneath a wing of the aircraft,
a turbomachine comprising an engine and a fan surrounded by a fan casing and positioned upstream of the engine, the turbomachine having a longitudinal direction X and a midplane XZ,
a nacelle surrounding the engine and the fan casing and further comprising a load bearer positioned at an upper part of the nacelle, a nose cowl fixed to a frontal zone of the fan casing forward of the load bearer and lateral cowls mounted in an articulated manner on each side of the load bearer,
a forward fan mount fixed between the frontal zone of the fan casing and a frontal zone of the load bearer,
a rear pylon mount fixed between the pylon and a rear part of the load bearer, and
a positioning assembly comprising a peg secured to an upper and rear part of the fan casing and extending vertically upwards, and an oblong hole made in a lower spar of the load bearer and into which hole the peg can be pushed, with the major axis of the oblong hole being parallel to the longitudinal direction X.

2. The propulsion assembly according to claim 1 , wherein the forward fan mount is fixed directly between the frontal zone of the load bearer and the frontal zone of the fan casing.

3. The propulsion assembly according to claim 2 , wherein the forward fan mount comprises, on each side of the midplane XZ, a first fitting secured to the fan casing, and a second fitting secured to the load bearer and in that the first fitting and the second fitting are mounted articulated relative to one another about an axis of rotation which is perpendicular to the midplane XZ.

4. The propulsion assembly according to claim 1 , wherein the forward fan mount is fixed between the frontal zone of the load bearer and the nose cowl which is fixed to the frontal zone of the fan casing.

5. The propulsion assembly according to claim 4 , wherein the forward fan mount comprises, on each side of the midplane XZ, a first fitting secured to the nose cowl, and a second fitting secured to the load bearer, and in that the first fitting and the second fitting are mounted articulated relative to one another about an axis of rotation which is perpendicular to the midplane XZ.

6. The propulsion assembly according to claim 1 , wherein the rear pylon mount comprises, on each side of the midplane XZ, a first yoke fitting fixed beneath a lower spar of the load bearer, a second yoke fitting fixed to the pylon and a link rod mounted in an articulated manner between the first yoke fitting and the second yoke fitting about an axis of rotation perpendicular to the midplane XZ.

7. An aircraft comprising at least one propulsion assembly according to claim 1 .

8. A propulsion assembly for an aircraft having a wing, a pylon, a fan casing, and a nacelle, the propulsion assembly comprising:
a load bearer having a distal end and a proximal end, and disposed at an upper part of the nacelle,
a nose cowl disposed on a frontal zone of the fan casing forward of the load bearer,
a pair of lateral cowls mounted pivotally mounted on each side of the load bearer,
a forward fan mount disposed between the frontal zone of the fan casing and the proximal end of the load bearer,
a rear pylon mount disposed between the pylon and the distal end of the load bearer, and
a guiding apparatus comprising a peg secured to an upper and rear part of the fan casing and extending vertically upwards, and an oblong aperture disposed in a lower spar of the load bearer, wherein the peg is configured to be disposed within the oblong aperture, and wherein the axis of the oblong aperture is parallel to a longitudinal direction.

9. The propulsion assembly according to claim 8 , wherein the forward fan mount is directly attached to the proximal end of the load bearer at a first end, and to the frontal zone of the fan casing at a second opposing end.

10. The propulsion assembly according to claim 9 , wherein the forward fan mount further comprises a first support attached to the fan casing, a second support attached to the load bearer, and wherein the first support and the second support are pivotably movable relative to one another about an axis of rotation perpendicular to a midplane of the propulsion assembly.

11. The propulsion assembly according to claim 9 , wherein the forward fan mount further comprises a third support attached to the nose cowl, and a fourth support attached to the load bearer, and wherein the third support and the fourth support are pivotably movable relative to one another about an axis of rotation perpendicular to a midplane of the propulsion assembly.

12. The propulsion assembly according to claim 8 , wherein the rear pylon mount further comprises a first yoke support attached beneath a lower spar of the load bearer, a second yoke support attached to the pylon, and a support rod having a first end and a second end, wherein the first end is pivotally mounted to the first yoke support and the second end is pivotally attached to the second yoke support about an axis of rotation perpendicular to a midplane of the propulsion assembly.

Assignees

• Airbus Operations Sas

Inventors

• Ridray Frédéric

Classifications

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/12

  within, or attached to, wings · CPC title

• B64C7/02

  Nacelles · CPC title