Riveted assembly and associated production method

Patent metadata

Field	Value
Publication number	US-10100859-B2
Application number	US-201515303924-A
Country	US
Kind code	B2
Filing date	Apr 8, 2015
Priority date	Apr 14, 2014
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.

First claim

The invention claimed is:

1. An assembly comprising a core, at least one first sheet held on one side of the core by a metallic rivet, and a second sheet held by the rivet on a side of the core opposite from the side of the first sheet, the rivet having two ends and at least a first one of these ends having a flared shape that extends at least through the entire thickness of the first sheet, a second of these ends having a flared shape that extends through at least the entire thickness of the second sheet, wherein the core includes a composite material, and the first sheet and the second sheet each includes a metallic material.

2. An assembly according to claim 1 , further comprising a metallic washer that includes a flared shape, and a first end configured to receive the first end of the metallic rivet, wherein the flared shape of the washer extends through the entirety of the first sheet into the core.

3. An assembly according to claim 1 , wherein the first end has an outside shape that is conical, with an angle at the apex lying in the range 60° to 130°.

4. An assembly according to claim 1 , wherein the outside surface of the first end is level with the outside surface of the first sheet.

5. An assembly according to claim 1 , including a bushing placed around an intermediate portion of the rivet, between the ends of the rivet.

6. A rotary or static part, optionally a streamlined part, of a turbine engine, the part comprising an assembly according to claim 1 .

7. A fabrication method for fabricating an assembly according to claim 1 , the method comprising the following steps:
providing a core, a first sheet, and a second sheet;
placing the first sheet on one side of the core;
placing the second sheet on a side of the core opposite from the side of the first sheet; and
riveting together the core, the first sheet, and the second sheet.

8. A fabrication method according to claim 7 , wherein, between the placing the first sheet and the riveting step, at least one hole is provided of flared shape that extends at least through the entire thickness of the first sheet.

9. A fabrication method according to claim 7 , wherein after the riveting step, the assembly is leveled so that the outside surface of the first end is level with the outside surface of the first sheet.

10. A fabrication method according to claim 7 , wherein, in the placing step, the first sheet is fastened to the core, in particular by adhesive.

11. A fabrication method according to claim 7 , wherein, in the riveting step, a washer is interposed between the rivet and the second sheet.

12. The method of claim 7 , wherein an entirety of the method is performed at a temperature of less than 120° C.

Assignees

• Safran Aircraft Engines

Inventors

• Savoyat Pierre
• Bourgeois Jean-Paul
• Dambrine Bruno
• Marlin François
• Raulin Dominique
• Servant Régis

Classifications

• F16B5/01

  by means of fastening elements specially adapted for honeycomb panels · CPC title

• F16B19/08

  Hollow rivets; Multi-part rivets · CPC title

• F16B19/1027

  Multi-part rivets · CPC title

• F16B5/04 Primary

  by means of riveting (rivets F16B19/04) · CPC title