DEVICE FOR FASTENING A FLUID TRANSPORT CIRCUIT TO AN ELEMENT OF THE STRUCTURE OF AN AIRCRAFT AND RELATED AIRCRAFT

• US 20130161940A1
• Filed: 11/29/2012
• Published: 06/27/2013
• Est. Priority Date: 11/30/2011
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Courpet, Alexis, ROSSATO, Robert
• Granted Patent: US 9,598,181 B2
• Time in Patent Office: Days
• US Class Current: 285/62
• CPC Class Codes: B64D 37/005 Accessories not provided for in the groups B64D37/02 - B64D37/28
• CPC Class Codes: B64D 45/02 Lightning protectors; Static dischargers in general H01T
• CPC Class Codes: B64D 47/00 Equipment not otherwise provided for
• CPC Class Codes: F16L 3/1222 the member having the form of a closed ring, e.g. used for the function of two adjacent pipe sections
• CPC Class Codes: F16L 39/005 for concentric pipes
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

The invention concerns a fastening device (10) for a fluid transport circuit to an element of the structure of an aircraft, with the fluid transport to circuit containing several portions (23, 42), each of which is made up of an external tube (22, 44) positioned around an internal tube (21, 43). The fastening device (10) is characterized in that the fastening device (10) is positioned at a connection (40) between two portions (23, 42) of the fluid transport circuit, and it contains a body (26) with a plate (27) intended to attach the fastening device (10) to the element (61) of the structure of the aircraft, this body (26) providing at least one sealed connection between the external tubes (22, 44) of the two portions (23, 42) and a support system guaranteeing appreciably constant radial clearance between the internal tube (21, 43) and the external tube (22, 44) of the two portions (23, 42) of the fluid transport circuit.

Claims

1. A circuit for the transport of a fluid in an aircraft, containing an internal tube (21, 43) surrounded by an external tube (22, 44), characterized in that it contains two portions (23, 42) connected by a fastening device (10) of the said circuit to the structure of the aircraft, in which:

a body (26) with a plate (27), including a cylindrical part (29, 62) of an appropriate diameter mechanically attached to the plate (27) and able to be connected in a sealed manner to an external tube (22, 44) and to the internal tube of said circuit by a support system (40, 75, 33, 30) that will guarantee a predetermined space between said internal and external tubes (21, 22, 43, 44) of the two portions (23, 42)

the plate contains a mechanical interface (32) that can be fixed to the structure (61) of an aircraft.

the plate (27) contains a mechanical interface (36) to fasten to a sleeve (46) associated with an external tube (22, 44) of the circuit and covering a junction of the body with an internal tube of one of the portions (21, 42) of the circuit.

2. A circuit according to claim 1, in which the support system is made up of a junction system (41) attached to the internal tube (21) that links the internal tube (21) to the side of one end of the body (26).

3. A circuit according to claim 1, in which the cylindrical part (29) of the body is welded to an end of an external tube (44) of one of the portions (23, 42)

4. The circuit, according to claim 1, in which the fastening device (10) includes an internal junction (62) passing through the body (26) and having a diameter appreciably equal to the diameter of the internal tube (21, 43) of the portions (23, 42) and where the support system is formed by at least one spacer piece (75) located between the body (26) and the internal junction (62), with the body (26), the internal junction (62) and the spacer piece (75) forming one single and like piece.

5. A circuit according to claim 4, in which the body (26), the internal junction (62) and the spacer piece (75) are manufacture by molding.

6. A circuit according to claim 1, in which the fastening device (10) is made of a conductive material that provides electrical continuity between the two portions (23, 42) and the structure of the aircraft when these portions are made of conductive materials.