STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT

• US 20110174919A1
• Filed: 08/05/2009
• Published: 07/21/2011
• Est. Priority Date: 10/01/2008
• Status: Active Grant

• Current Assignee: Safran Nacelles
• Original Assignee: Aircelle (Safran SA)
• Inventors: Vauchel, Guy Bernard, Caruel, Pierre
• Granted Patent: US 8,840,061 B2
• Time in Patent Office: Days
• US Class Current: 244/54
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2260/50 Kinematic linkage, i.e. transmission of position
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

Claims

1. A strut adapted to support an aircraft turbojet engine nacelle, comprising:

a connecting part for connection between a casing of fan or a casing of a gas generator of said turbojet engine and a wing of said aircraft, and

a Y-shaped box-section part, secured to said connecting part and adapted to form an upper part of an internal fixed structure of said nacelle.

2. The strut according to claim 1, wherein said box-structure part comprises ventilation orifices.

3. The strut according to claim 1, wherein said connecting part comprises a cross-piece supporting connecting cones with said casing of the fan.

4. The strut according to claim 1, wherein said box-section part includes connecting platens for connection to said gas generator.

5. An aircraft turbojet engine nacelle incorporating a strut according to claim 1 in a downstream portion thereof, in which the connecting part of the strut is adapted to be fixed on said casing of the fan or on said casing of the gas generator, and thrust recovery connecting rods extending to an inside of the box-section part of said strut to cooperate with said casing of the gas generator.

6. The aircraft turbojet engine nacelle incorporating a strut according to claim 3 in a downstream portion, not having thrust recovery connecting rods inside said box-section part.

7. The nacelle according to claim 5, wherein said downstream portion includes a grid thrust reverser.

8. The nacelle according to claim 7, wherein said reverser comprises a grid support structure comprising two upper halves fixed on said fan casing and connected to each other by connecting rods passing through the connecting part of said strut.

9. The nacelle according to claim 8, wherein said grid support structure also comprises two lower halves pivotably mounted on said upper halves between a service position and a maintenance position.

10. The nacelle according to claim 9, wherein said lower halves incorporate upstream panels defining the upstream lower part of the internal fixed structure of the nacelle, as a complement to said box-section part.

11. The nacelle according to claim 10, also comprising a quasi-annular panel defining the downstream lower part of the internal fixed structure of the nacelle, this panel being slidingly mounted on said box-section part between a service position in which it adjoins said upstream panels, and a maintenance position in which it is spaced away downstream from said upstream panels.

12. The nacelle according to claim 7, further comprising a cowl slidingly mounted on the connecting part of said strut between a direct jet position, in which said cowl covers said grids, and a reversed jet position, in which this cowl uncovers said grids.

13. The nacelle according to claim 12, wherein said cowl comprises two upper halves slidingly mounted on the connecting part of said strut, cooperating with at least two upper actuators, and a lower part slidingly mounted on said upper halves between an upstream service position and a downstream maintenance position.

14. The nacelle according to claim 13, comprising a lower actuator cooperating with said lower cowl part.

15. The nacelle according to claim 13, comprising a frame connecting said two upper cowl halves to each other, and a lower actuator cooperating with said frame.

16. The nacelle according to claim 5, comprising a thrust reverser with doors comprising two half-panels defining the internal fixed structure of the nacelle, these two half-panels being able to move between a service position and a maintenance position using a system of connecting rods and guideways.

17. The nacelle according to claim 7, of the S-shaped secondary flow stream type, comprising two internal structure half-panels articulated on said strut and two mobile half-cowls slidingly mounted on rails themselves pivotably mounted on said strut.

18. The nacelle according to claim 7, comprising two half-panels and two half-rings defining an internal fixed structure of the nacelle, and two mobile half-cowls provided with thrust reverser cover doors on their trailing edges, connected by connecting rods to said half-rings, said half-panels being articulated on said strut, and the assemblies formed by said mobile half-cowls and by said half-rings being slidingly mounted on rails, themselves pivotably mounted on said strut.

19. A propulsion assembly comprising a nacelle according to claim 5, and a turbojet engine housed inside said nacelle and cooperating with a part of said strut.