Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle

Patent metadata

Field	Value
Publication number	US-9315275-B2
Application number	US-201213563858-A
Country	US
Kind code	B2
Filing date	Aug 1, 2012
Priority date	Aug 5, 2011
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

An aircraft nacelle includes a first conduit for an air inlet and a second conduit for an engine, arranged end to end and connected by an annular flange, attached to the air inlet, and an annular flange, attached to the engine. The annular flanges are connected by a plurality of passage holes in the annular flanges and arranged in line with each other. Rods are housed in the passage holes. For at least one rod, the passage hole of one of the annular flanges has a diameter greater than the diameter of the rod allowing the rod to move in case of deformation of one of the two conduits. An angle profile is inserted between the rod and a cylindrical portion adjacent to the annular flange and is connected to the adjacent cylindrical portion through the intermediary of at least one mechanism for absorbing eventual deformations in radial direction.

First claim

The invention claimed is:

1. An aircraft nacelle comprising:
a first conduit for an air inlet;
a second conduit for an engine; and
a fastening device;
wherein the first and second conduits are arranged end to end and connected by the fastening device;
wherein the fastening device comprises:
a first annular flange attached to the air inlet;
a second annular flange attached to the engine;
wherein, said first and second annular flanges comprise a first and a second pluralities of passage holes, defined in the annular flanges and arranged in line with each other, and
first fastening elements comprising a plurality of rods housed in the passage holes,
wherein, for at least one first fastening element, the passage hole of one of the first and second annular flanges has a diameter greater than the diameter of one of the plurality of rods, allowing said one rod to move in case of deformation of one of the first and second conduits and the passage hole of the other of the first and second annular flanges has a diameter adapted to the diameter of the one rod,
wherein an angle profile is inserted between the first fastening element and a cylindrical portion adjacent to said first annular flange,
wherein said angle profile is connected to the adjacent cylindrical portion through the intermediary of at least one second fastening element comprising a means for absorbing eventual deformations in a radial direction,
wherein the second fastening element further comprises a deformable element inserted entirely between the angle profile and a shoulder solidly attached to said second fastening element.

2. The nacelle according to claim 1 , wherein the greater diameter of the passage hole is configured to allow said one rod a displacement greater than or equal to 5 mm.

3. The nacelle according to claim 1 , wherein the axis of the passage hole of the annular flange with an enlarged diameter is offset towards the exterior relative to the axis of the passage hole of the other annular flange.

4. The nacelle according to claim 1 , wherein the second fastening element comprises a rod with axis oriented in the radial direction.

5. The nacelle according to claim 1 , wherein the angle profile comprises a passage hole adapted to the diameter of the one rod of the first fastening element.

6. The nacelle according to claim 5 , wherein the deformable element is configured to generate a force on the angle profile with a tendency to oppose the radial movement towards the exterior of said angle profile, whereby said force is proportional to the displacement of the first fastening element.

7. The nacelle according to claim 6 , wherein the deformable element is a deformable bushing with a relatively thin wall thickness in a central part so that the bushing can deform.

8. The nacelle according to claim 7 , wherein the height of the deformable bushing is inversely proportional to the distance separating the second fastening element from a wing of the angle profile locating against the first annular flange.

9. The nacelle according to claim 1 , wherein the angle profile is connected to the adjacent cylindrical portion through the intermediary of two second fastening elements arranged in symmetric manner relative to the first fastening element.

Assignees

• Porte Alain
• Lambert David
• Le Flem Franck
• Airbus Operations Sas

Inventors

• Porte Alain
• Lambert David
• Le Flem Franck

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title