Anterior part of a nacelle of an aircraft propulsion unit having a shock absorbing element

Patent metadata

Field	Value
Publication number	US-11293302-B2
Application number	US-201816229500-A
Country	US
Kind code	B2
Filing date	Dec 21, 2018
Priority date	Dec 21, 2017
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.

First claim

The invention claimed is:

1. An anterior part of a nacelle of an aircraft propulsion unit, the anterior part having a front end allowing air to enter and a rear end, comprising:
an air inlet lip arranged at the front end,
an internal structure extending an interior surface of the air inlet lip,
an external panel extending an exterior surface of the air inlet lip,
a rigidifying frame that is annular about an axis of revolution, the rigidifying frame comprising an external peripheral edge connected to the external panel,
wherein the level at which the connection to the engine of the propulsion unit is made not being defined by the internal structure, the bottom part of the anterior part of the nacelle comprises a shock-absorbing element interposed between an internal peripheral edge of the rigidifying frame and the internal structure, connected rigidly to an internal peripheral edge of the rigidifying frame at a first point and to the internal structure at a second point, the internal peripheral edge of the rigidifying frame being connected to the engine.

2. The anterior part of a nacelle according to claim 1 , wherein the shock-absorbing element further comprises a deformable structure formed in full or in part from a composite material or from a metal/composite hybrid material.

3. The anterior of a nacelle according to claim 1 , further comprising a rear bracket having a first end connected to the rigidifying frame at the internal peripheral edge thereof.

4. The anterior part of a nacelle according to claim 3 , wherein the first end of the rear bracket is also connected to the shock-absorbing element by a common join.

5. The anterior part of a nacelle according to claim 4 , wherein the rear bracket further comprises a second end having a rear flange designed to be fixed to an engine pad bracket of the aircraft engine.

6. The anterior part of a nacelle according to claim 5 , wherein the shock-absorbing element has a structure that is deformable under the effect of an impact coming from inside the anterior part, so that deformation of the deformable structure absorbs the energy of the impact in order to protect the rear bracket.

7. The anterior part of a nacelle according to claim 6 , wherein the deformable structure is deformable in such a way that deformation of the deformable structure absorbs the impact energy of a fan blade of the engine detaching from the fan at a maximum speed of the engine.

8. The anterior part of a nacelle according to claim 1 , wherein the shock-absorbing element has, in cross section, two branches connected to a common vertex connected to the rigidifying frame at one end and, connect to two vertices connected to the internal structure at a second end.

9. The anterior part of a nacelle according to claim 8 , wherein the shock-absorbing element has a triangular cross section with one vertex connected to the rigidifying frame and the other two vertices connected to the internal structure.

10. The anterior part of a nacelle according to claim 8 , wherein each branch of the shock-absorbing element has, in cross section, a portion in the shape of a circular arc extending between the first vertex and the internal structure.

11. The anterior part of a nacelle according to claim 8 , wherein each branch of the shock-absorbing element has, in cross section, a complex shape with programmed deformation comprising a succession of concave portions and of convex portions.

12. The anterior part of a nacelle according to claim 8 , wherein at least one of the branches is formed from at least two different materials.

13. The anterior part of a nacelle according to claim 8 , wherein the shock-absorbing element is connected to the rigidifying frame by a first extension surface configured to bear against the rigidifying frame, and the shock-absorbing element is connected to the internal structure by a second and a third extension surface respectively configured to bear against the internal structure.

14. An aircraft propulsion unit comprising a nacelle having an anterior part (P 1 ) according to claim 1 .

15. An anterior part of a nacelle of an aircraft propulsion unit, the anterior part having a front end allowing air to enter and a rear end, comprising:
an air inlet lip arranged at the front end,
an internal structure extending an interior surface of the air inlet lip,
an external panel extending an exterior surface of the air inlet lip,
a rigidifying frame that is annular about an axis of revolution, the rigidifying frame comprising an external peripheral edge connected to the external panel,
wherein the level at which the connection to the engine of the propulsion unit is spaced apart from the internal structure, the bottom part of the anterior part of the nacelle comprises a shock-absorbing element interposed between an internal peripheral edge of the rigidifying frame and the internal structure, connected rigidly to an internal peripheral edge of the rigidifying frame at a first point and to the internal structure at a second point, the internal peripheral edge of the rigidifying frame being connected to the engine.

16. The anterior part of a nacelle according to claim 15 , wherein the shock-absorbing element further comprises a deformable structure formed in full or in part from a composite material or from a metal/composite hybrid material.

17. The anterior of a nacelle according to claim 15 , further comprising a rear bracket having a first end connected to the rigidifying frame at the internal peripheral edge thereof.

18. The anterior part of a nacelle according to claim 17 , wherein the first end of the rear bracket is also connected to the shock-absorbing element by a common join.

19. The anterior part of a nacelle according to claim 18 , wherein the rear bracket further comprises a second end having a rear flange designed to be fixed to an engine pad bracket of the aircraft engine.

20. The anterior part of a nacelle according to claim 19 , wherein the shock-absorbing element has a structure that is deformable under the effect of an impact coming from inside the anterior part, so that deformation of the deformable structure absorbs the energy of the impact in order to protect the rear bracket.

Assignees

• Airbus Operations Sas

Inventors

• Vinches Frédéric
• Albet Gregory
• Sentier Julien

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• B64D2033/022

  comprising bird or foreign object protections · CPC title

• F02C7/04

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

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title