AERODYNAMIC FAIRING DIVIDED INTO SUB-PORTIONS

• US 20150144732A1
• Filed: 09/30/2014
• Published: 05/28/2015
• Est. Priority Date: 11/25/2013
• 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: Voyer, Nicolas, Peyruseigt, Francois, Gaches, Thierry, Kaleta, Mathieu, Chamaillard, Delphine
• Granted Patent: US 9,469,409 B2
• Time in Patent Office: Days
• US Class Current: 244/54
• CPC Class Codes: B64C 1/0009 Aerodynamic aspects
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C
• 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

Abstract

An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.

Claims

1. An aerodynamic fairing of a pylon of a turbo engine comprising:

the fairing being in the form of a casing which extends along a longitudinal axis and which comprises a first lateral panel and a second lateral panel which are substantially parallel with the longitudinal axis and which are distributed at one side and the other of a plane of symmetry of the fairing,

the aerodynamic fairing comprising at least two sub-assemblies which are arranged consecutively along the longitudinal axis and which are separated from each other by a gap,

each sub-assembly comprising a frame which is oriented transversely relative to the longitudinal axis and a floor portion which extends along the longitudinal axis,

each frame having, in a position for use, an upper edge, a lower edge which is fixed to an inner face of the floor portion of the sub-assembly, and a first lateral edge and a second lateral edge to which the first lateral panel and the second lateral panel are fixed, respectively.

2. The aerodynamic fairing as claimed in claim 1, wherein two floor portions which are directly consecutive along the longitudinal axis are spaced apart by a distance of between 0.1 mm and 5 cm.

3. The aerodynamic fairing as claimed in claim 1, wherein the sub-assembly is a first sub-assembly and a plate is fixed at the inner face of the floor portion of the first sub-assembly, the plate covering a gap between the first sub-assembly and a second sub-assembly which is directly consecutive to the first sub-assembly.

4. The aerodynamic fairing as claimed in claim 1, wherein at least one floor portion comprises a reinforcement member which extends transversely to the longitudinal axis.

8. The aerodynamic fairing as claimed in claim 1, wherein at least one floor portion comprises a reinforcement member extending transversely to the longitudinal axis.

5. An aerodynamic fairing of a turbo engine pylon comprising:

a casing extending along a longitudinal axis and comprising a first lateral panel and a second lateral panel both substantially parallel to the longitudinal axis and being arranged at one side and the other of a plane of symmetry of the fairing,

at least two sub-assemblies arranged along the longitudinal axis and being separated from each other by a gap,

each sub-assembly comprising a frame extending transversely relative to the longitudinal axis and a floor portion extending along the longitudinal axis,

each frame having, in a position for use, an upper edge, a lower edge fixed to an inner face of the floor portion of the sub-assembly, a first lateral edge to which the first lateral panel is fixed, and a second lateral edge to which the second lateral panel is fixed.

6. The aerodynamic fairing as claimed in claim 5, wherein two floor portions of two sub-assemblies which are directly adjacent along the longitudinal axis are spaced apart by a distance in the range of 0.1 mm to 5 cm.

7. The aerodynamic fairing as claimed in claim 5, wherein the sub-assembly is a first sub-assembly and a plate is fixed at the inner face of the floor portion of the first sub-assembly, the plate covering a gap between the first sub-assembly and a second sub-assembly which is directly adjacent to the first sub-assembly.