Aircraft turbojet engine nacelle comprise an increased-rigidity air intake

Patent metadata

Field	Value
Publication number	US-9845707-B2
Application number	US-201414575392-A
Country	US
Kind code	B2
Filing date	Dec 18, 2014
Priority date	Jan 3, 2014
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.

First claim

The invention claimed is:

1. An aircraft turbojet engine nacelle comprising:
an air intake assembly of substantially annular shape and comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure,
the annular rear structure comprises, arranged concentrically:
one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone,
at least one connecting ring which provides a connection with at least one of the external and internal walls, said connecting ring extending from the hollow casing, in the form of a third annular zone.

2. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the monolithic panel or panels are curved.

3. The aircraft turbojet engine nacelle as claimed in claim 2 , wherein the monolithic panel or panels have a convex side facing toward the downstream end of the nacelle.

4. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the monolithic panel or panels are made of composite materials.

5. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein said at least one connecting ring is made of titanium.

6. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the annular rear structure comprises one or more reinforcing elements reinforcing said at least one connecting ring.

7. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the at least one monolithic panel and the connecting ring are arranged successively.

8. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the
at least one monolithic panel comprises a first hollow casing and a second hollow casing, said hollow casings being positioned respectively on the outer and inner peripheral edges of said at least one panel.

9. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the one or more hollow casings form an integral part of the monolithic panel or panels.

10. The aircraft turbojet engine nacelle as claimed in claim 1 , wherein the one or more hollow casings extend 360 degrees around the annular rear structure.

11. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the monolithic panel or panels are made of composite materials.

12. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein said at least one connecting ring is made of titanium.

13. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the annular rear structure comprises one or more reinforcing elements reinforcing said at least one connecting ring.

14. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the at least one monolithic panel comprises a first hollow casing and a second hollow casing, said hollow casings being positioned respectively on the outer and inner peripheral edges of said at least one panel.

15. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the one or more hollow casings form an integral part of the monolithic panel or panels.

16. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the one or more hollow casings extend 360 degrees around the annular rear structure.

17. An aircraft which comprises at least one aircraft turbojet engine nacelle comprising:
an air intake assembly of substantially annular shape and comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure,
the annular rear structure comprises, arranged concentrically:
one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone,
at least one connecting ring which provides a connection with at least one of the external and internal walls, said connecting ring extending from the hollow casing, in the form of a third annular zone,
wherein the monolithic panel or panels are curved and have a convex side facing toward the downstream end of the nacelle.

18. An aircraft turbojet engine nacelle comprising:
an air intake assembly of substantially annular shape and comprising an external wall connected to an internal wall by an air intake lip and by an annular rear structure,
the annular rear structure comprising:
one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone,
at least one connecting ring which provides a connection with at least one of the external and internal walls, said connecting ring extending from the hollow casing, in the form of a third annular zone, and
one or more reinforcing elements reinforcing said at least one connecting ring.

19. The aircraft turbojet engine nacelle as claimed in claim 10 , wherein the monolithic panel or panels are curved.

20. The aircraft turbojet engine nacelle as claimed in claim 19 , wherein the monolithic panel or panels have a convex side facing toward the downstream end of the nacelle.

Assignees

• Airbus Operations Sas

Inventors

• Porte Alain
• Fargues Matthieu

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F01D25/005

  Selecting particular materials · CPC title