Intake for an engine of an aircraft

Patent metadata

Field	Value
Publication number	US-9889945-B2
Application number	US-201314649754-A
Country	US
Kind code	B2
Filing date	Dec 2, 2013
Priority date	Dec 5, 2012
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

An intake for feeding air to an engine of an aircraft includes an opening for sucking in air, which opening faces in the direction of movement of the aircraft; and an air duct between the opening and the engine, which air duct is curved such that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft. An object flying into the opening contacts the impact region. The impact region has a penetration region, which is designed to be penetrated by the impinging object.

First claim

The invention claimed is:

1. An intake for feeding air to an engine of an aircraft, comprising:
an opening for sucking in air, the opening facing a direction of movement of the aircraft; and
an air duct between the opening and the engine, wherein the air duct is curved in a way that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft, such that an object flying into the opening contacts the impact region;
wherein the impact region has a predetermined breaking region, which is arranged in a shell-shaped part of the intake, and wherein the predetermined breaking region protrudes from the aircraft and is designed to separate from the aircraft upon impact of a bird as the impinging object.

2. The intake as claimed in claim 1 ,
wherein at least part of the intake protrudes from the aircraft;
wherein the predetermined breaking region is arranged in the part of the intake protruding from the aircraft.

3. The intake as claimed in claim 2 ,
wherein the part of the intake protruding from the aircraft is separated from the aircraft upon impact of the object.

4. The intake as claimed in claim 1 ,
wherein the predetermined breaking region extends from an inner wall of the air duct to an outer wall of the intake, such that the object contacting the predetermined breaking region penetrates the predetermined breaking region and leaves the aircraft.

5. The intake as claimed in claim 1 ,
wherein the predetermined breaking region comprises a cavity, in which the object contacting the predetermined breaking region is stopped.

6. The intake as claimed in claim 1 ,
wherein the predetermined breaking region comprises a material that at least partially absorbs an impact energy of the object.

7. The intake as claimed in claim 1 ,
wherein the predetermined breaking region comprises a first material, which is designed to absorb a first part of an impact energy of the impinging object, and comprises a second material, which is arranged after the first material in relation to the direction of movement of the aircraft and which is designed to absorb a remaining part of the impact energy.

8. The intake as claimed in claim 5 ,
wherein a material for absorbing an impact energy is arranged in the cavity that serves to stop the object.

9. The intake as claimed in claim 1 ,
wherein a deflection ramp is arranged in the predetermined breaking region and is configured to deflect the object penetrating the predetermined breaking region in a first direction into another direction.

10. The intake as claimed in claim 1 ,
wherein the predetermined breaking region comprises a flap, which in a closed position provides part of an inner wall of the air duct.

11. The intake as claimed in claim 10 ,
wherein the flap is preloaded by a spring mechanism, such that the flap closes the inner wall of the air duct following an infiltration of the object into the predetermined breaking region.

12. The intake as claimed in claim 1 ,
wherein a surface of the predetermined breaking region in the air duct is provided with a radar-absorbing material.

13. The intake as claimed in claim 1 ,
wherein the air duct in a surrounding environment of the predetermined breaking region has a curvature through at least 90°.

14. An aircraft, comprising:
an engine;
an intake for feeding air into the engine, the intake comprising
an opening for sucking in air, the opening facing a direction of movement of the aircraft; and
an air duct between the opening and the engine, wherein the air duct is curved in a way that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft, such that an object flying into the opening contacts the impact region;

wherein the impact region has a predetermined breaking region, which is arranged in a shell-shaped part of the intake, and wherein the predetermined breaking region protrudes from the aircraft and is designed to separate from the aircraft upon impact of a bird as the impinging object;
wherein the engine is arranged offset in relation to the opening of the intake.

15. The aircraft as claimed in claim 14 ,
wherein the engine is arranged in an opposite direction of movement of the aircraft.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Judas Michael
• Bichler Bartholomaeus

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/022

  comprising bird or foreign object protections · CPC title

• F02C7/05

  having provisions for obviating the penetration of damaging objects or particles · CPC title