Aircraft propulsion assembly having a jet engine, a pylon and means for attaching the jet engine to the pylon

Patent metadata

Field	Value
Publication number	US-12448137-B2
Application number	US-202418740984-A
Country	US
Kind code	B2
Filing date	Jun 12, 2024
Priority date	Jun 14, 2023
Publication date	Oct 21, 2025
Grant date	Oct 21, 2025

Abstract

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, said propulsion assembly comprising:
a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis,
an attachment pylon having a rigid structure that takes a form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall,
a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and
a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar,
wherein the front engine attachment comprises on each side of the vertical median plane, a pair of first rods,
wherein a first end of each first rod is mounted in a first articulated manner on the lower end of the front wall, and
wherein a second end of each first rod is mounted in a second articulated manner on the upper area of the central casing,
wherein the second ends of the first rods are closer to the vertical median plane than the first ends.

2. The propulsion assembly according to claim 1 , further comprising:
a main rod fixed between the upper spar and the front wall.

3. The propulsion assembly according to claim 1 , wherein for each first rod, the propulsion assembly comprises a second rod a first end of which is mounted in a third articulated manner on the lower end of the front wall and a second end of which is mounted in a fourth articulated manner on the upper area of the central casing.

4. The propulsion assembly according to claim 1 , wherein the complementary front engine attachment comprises a lever movably mounted on the front end of the upper spar at the vertical median plane and first and second ends of the lever are movably mounted to the upper area of the fan casing on opposite sides of the vertical median plane, the lever movably mounted at the vertical median plane and the first and second ends movably mounted on opposite sides of the vertical median plane each providing at least a rotation around an axis parallel to the longitudinal axis.

5. An aircraft comprising:
a wing, and
the propulsion assembly according to claim 1 ,
wherein the rigid structure is fastened beneath the wing.

6. A propulsion assembly for an aircraft, said propulsion assembly comprising:
a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis,
an attachment pylon having a rigid structure that takes a form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall,
a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and
a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar,
wherein the front engine attachment comprises on each side of the vertical median plane, a pair of first rods,
wherein a first end of each first rod is mounted in a first articulated manner on the lower end of the front wall, and
wherein a second end of each first rod is mounted in a second articulated manner on the upper area of the central casing,
wherein for each first rod, the propulsion assembly comprises a second rod a first end of which is mounted in a third articulated manner on the lower end of the front wall and a second end of which is mounted in a fourth articulated manner on the upper area of the central casing,
wherein the first ends of the second rods are closer to the vertical median plane than the second ends.

7. A propulsion assembly for an aircraft, said propulsion assembly comprising:
a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis,
an attachment pylon having a rigid structure that takes a form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall,
a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and
a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar,
wherein the front engine attachment comprises on each side of the vertical median plane, a pair of first rods,
wherein a first end of each first rod is mounted in a first articulated manner on the lower end of the front wall,
wherein a second end of each first rod is mounted in a second articulated manner on the upper area of the central casing,
wherein the complementary front engine attachment comprises a plate assembly movably mounted on the front end of the upper spar at the vertical median plane and first and second ends of the plate assembly are movably mounted to the upper area of the fan casing on opposite sides of the vertical median plane, the plate assembly movably mounted at the vertical median plane and the first and second ends movably mounted on opposite sides of the vertical median plane each providing at least a rotation around an axis parallel to a vertical axis.

Assignees

• Airbus Operations Sas

Inventors

• Deforet Thomas
• Journade Frédéric
• Mahe Mathieu
• Claveyrollas Antoine
• Kaleta Mathieu
• Renaud Eric

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• F02C7/20

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

• B64D27/18

  within, or attached to, wings · CPC title

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• B64C3/32

  specially adapted for mounting power plant · CPC title