Turboprop carrier structure and an assembly including such a carrier structure

• US 20040227033A1
• Filed: 02/19/2004
• Published: 11/18/2004
• Est. Priority Date: 02/19/2003
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma Moteurs
• Inventors: Picard, Jean-Louis, Mazeaud, Georges
• Granted Patent: US 7,100,869 B2
• Time in Patent Office: Days
• US Class Current: 244/54
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 29/02 associated with wings wings adapted for mounting power plant B64C
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: B64D 29/08 Inspection panels for power plants

Abstract

The carrier structure of the invention is used for carrying a turboprop and it is designed to be mounted beneath and/or in front of an airplane wing. In characteristic manner, said carrier structure comprises:

a top portion comprising a front arch, a rear arch, and longitudinal beams;

an upwardly-open removable bottom portion comprising at least two bottom arches and longerons;

said bottom portion being demountably fixed to the top portion by centering and fixing means, said bottom and top portions together defining a housing suitable for receiving said turboprop, and

a suspension for carrying said turboprop.

Claims

1. A carrier structure for a turboprop, the turboprop having a front portion comprising a fan, a central portion, and a rear portion, and being designed to be mounted in a longitudinal direction beneath and/or in front of an airplane wing, said wing having a framework, the carrier structure comprising:

a downwardly-open top portion for securely mounting to the framework of said wing and comprising a front arch from which said front portion of the turboprop is to be suspended, a rear arch, and longitudinal beams disposed at least between said front arch and said rear arch and suitable for extending as far as the framework of said wing, said longitudinal beams interconnecting said front arch and said rear arch and being designed to be secured to the framework of said wing;

a removable, upwardly-open bottom portion having at least two bottom arches together with longerons extending in the longitudinal direction and interconnecting said bottom arches;

said bottom portion being demountably secured to the top portion by centering and fixing means, said bottom and top portions together defining a housing suitable for receiving said turboprop; and

a suspension for carrying said turboprop.

2. A carrier structure according to claim 1, wherein said front arch and said rear arch of the top portion are each extended in a vertical plane by a respective one of the bottom arches.

3. A carrier structure according to claim 1, wherein said top portion further comprises at least one intermediate arch mounted on said longitudinal beams between said front arch and said rear arch.

4. A carrier structure according to claim 1, wherein said top portion further comprises a top cowling assembly disposed on the outside going from said framework of said wing at least as far as said front arch, while leaving an opening for placing longitudinally in line with the fan of the turboprop.

5. A carrier structure according to claim 4, wherein said top cowling assembly includes at least one hinged cover capable of being opened to give access to said housing containing said turboprop.

6. A carrier structure according to claim 1, wherein said bottom portion further comprises a bottom cowling assembly disposed on the outside going from said framework of said wing-at least as far as said front arch, leaving an opening for placing longitudinally in line with the fan of the turboprop.

7. A carrier structure according to claim 1, wherein said centering and fixing means comprise at least four centering and fixing assemblies disposed in a plane separating said top and bottom portions, each centering and fixing assembly comprising at least one centering pin and a corresponding hole, together with a locking device.

8. A carrier structure according to claim 7, wherein said locking device comprises at least one screw co-operating with a corresponding thread and/or bore.

9. A carrier structure according to claim 1, wherein said suspension comprises a front suspension mounted on said front arch of the top portion.

10. A carrier structure according to claim 9, wherein said front suspension comprises at least two fixing areas disposed symmetrically on said front arch of the top portion and connected to said front portion of the turboprop via respective tabs.

11. A carrier structure according to claim 1, wherein said suspension comprises a front suspension mounted on the bottom portion.

12. A carrier structure according to claim 1, wherein said suspension further comprises, on the longitudinal beams of the top portion, a rear suspension for flexibly retaining the rear portion of the turboprop.

13. A carrier structure according to claim 12, wherein said rear suspension comprises two assemblies disposed symmetrically and transversely to the longitudinal direction, each assembly comprising first and second links together with an upright interconnecting at least two longitudinal beams of the top portion, the first and second links each having an outside end, and an inside end, said inside end of the first link and said inside end of the second link being mounted on the rear portion of the turboprop one above the other, and said outside ends of the first and second links being connected to said upright.

14. A carrier structure according to claim 12, wherein said rear suspension comprises two assemblies disposed symmetrically and transversely to the longitudinal direction, each assembly comprising first and second links and a pivot support connected to a longitudinal beam of the top portion, the first and second links each having an outside end and an inside end, said inside end of the first link and said inside end of the second link being mounted on the rear portion of the turboprop one above the other, and said outside ends of the first and second links being connected to at least one of the longitudinal beams of the top portion.

15. An assembly comprising a structure according to claim 1, an airplane wing to which said structure is fixed, and a turboprop disposed in said housing.