Extruded products for aeroplane floors made of an aluminium-copper-lithium alloy

Patent metadata

Field	Value
Publication number	US-2016368588-A1
Application number	US-201415100803-A
Country	US
Kind code	A1
Filing date	Dec 10, 2014
Priority date	Dec 13, 2013
Publication date	Dec 22, 2016
Grant date	—

Abstract

The invention relates in particular to an unprocessed extruded product for manufacturing a machined extruded product for the aeronautical industry, made of an Al—Cu—Li alloy. The invention also relates to the method for manufacturing a machined extruded product and to the corresponding machined extruded product. The products according to the invention are useful in particular for manufacturing floor beams and girders.

First claim

1 . Method for manufacturing a machined extruded product for the aeronautical industry having a machined core and at least one machined flank wherein
(a) a raw form made of an Al—Cu—Li alloy is cast with the following composition, as weight percentages: Cu: 2.0-6.0; Li: 0.5-2.0; Mg: 0-1.0; Ag: 0-0.7; Zn 0-1.0; and at least one element selected among Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si≦0.1; Fe≦0.1; others ≦0.05 each and ≦0.15 in total, the balance being aluminum, (b) said raw form is homogenized, (c) said raw form is hot worked by extrusion in such a way as to obtain a raw extruded product having a raw core and at least one raw flank. (d) said raw extruded product is solution-heat treated (e) said raw extruded product solution-heat treated is quenched, (f) said raw extruded product is stretched in a controlled manner (g) optionally a straightening or a forming of said extruded product is carried out, (h) said raw extruded product is artificially aged (i) said raw extruded product is machined in order to obtain a machined extruded product having a machined core and at least one machined flank corresponding to the raw flank wherein the dimension of said raw flank of which the direction is perpendicular to the dimension of the length of said raw core is at least 20% greater than the length of said machined flank.

2 . Method according to claim 1 wherein the thickness of the raw core that was machined on the face corresponding to a raw flank and the dimension of said raw flank of which the direction is perpendicular to the dimension of the length, as such that their sum is more than 50% greater optionally more than 80% greater than the length of the machined flank.

3 . Method according to claim 1 wherein a portion of said raw flank connecting said raw flank to said raw core has a decreasing thickness and in that the ratio of the thickness of said raw flank for the end of said raw flank connected to the core and for the end thereof opposite the core, is less than 0.8 and optionally less than 0.6 thus defining two substantially symmetrical concave areas.

4 . Method according to claim 3 wherein said portion of said raw flank for which the thickness is decreasing extends over a length less than 30% of the total length of the flank.

5 . Method according to claim 3 wherein the angle (α) between the lengthwise direction of the raw core and the direction corresponding to the decrease in the thickness of the flank is 45 +/−10°.

6 . Raw extruded product for the manufacture of a machined extruded product for the aeronautical industry,
made of an Al—Cu—Li alloy with the following composition, as weight percentages: Cu: 2.0-6.0; Li: 0.5-2.0; Mg: 0-1.0; Ag: 0-0.7; Zn 0-1.0; and at least one element selected among Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si≦0.1; Fe≦0.1; others ≦0.05 each and ≦0.15 in total, the balance being aluminum, having a raw core of which the aspect ratio is at least 5 and at least one raw flank of which the aspect ratio is less than 4 and of which the direction of the length is substantially perpendicular to the lengthwise direction of the core, wherien a portion of said raw flank connecting said raw flank to said raw core has a decreasing thickness and in that the ratio of the thickness of said raw flank for the end of said raw flank connected to the core and for the end thereof opposite the core, is less than 0.8 and optionally less than 0 6 thus defining two substantially symmetrical concave areas; the aspect ratio of the raw core or of the raw flank being the ratio L/E where L corresponds to the greatest dimension of the basic rectangle defined in the cross-section of the raw core or of the raw flank respectively and E corresponds to the smallest dimension of the basic rectangle defined in the cross-section of the raw core or of the raw flank respectively.

7 . Raw extruded product according to claim 6 wherein said portion of said raw flank for which the thickness is decreasing extends over a length less than 30% of the total length of the flank.

8 . Raw extruded product according to claim 6 wherein the angle (α) between the lengthwise direction of the raw core the direction corresponding to the decrease in the thickness of the flank is 45+/−10°.

9 . Raw extruded product according to claim 6 wherein the radius of curvature for the connection of said raw flank and of the core is between 2 and 4 mm

10 . Machined extruded product for the aeronautical industry able to be obtained by the method according to any of claim 1 , made of an Al—Cu—Li alloy with the following composition, as weight percentages: Cu: 2.0-6.0; Li: 0.5-2.0; Mg: 0-1.0; Ag: 0-0.7; Zn 0-1.0; and at least one element selected among Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si≦0.1; Fe≦0.1; others ≦0.05 each and ≦0.15 in total, the balance being aluminum,
having a machined core of which the aspect ratio is at least 20 and at least one machined flank of which the aspect ratio is less than 15 and of which the direction of the length is substantially perpendicular to the lengthwise direction of the core, wherein a granular structure thereof has a rate of recrystallized grains less than 10% and in that between the mid-length of said machined flank and said machined core the direction of the length of the grain is substantially parallel to the lengthwise direction of the flank,
the aspect ratio of the machined core or of the machined flank being the ratio L/E where L corresponds to the greatest dimension of the basic rectangle defined in the cross-section of the machined core or of the machined flank respectively and E corresponds to the smallest dimension of the basic rectangle defined in the cross-section of the machined core or of the machined flank respectively.

11 . Machined extruded product according to claim 10 wherein the difference between the direction of the length of the grains and the direction of the length of the flanks is less than 10°.

12 . Use of a A machined extruded product according to claim 10 as a structural element for aeronautical construction.

13 . Product according to claim 12 as a wing stiffener, fuselage stiffener, fuselage frame, floor beam or a floor cross beam, optionally a floor cross beam.

Assignees

• Constellium Issoire

Inventors

• PIGNATEL Jérome
• POUGET Gaëlle

Classifications

• C22C21/00

  Alloys based on aluminium · CPC title

• B21C23/142

  Making profiles · CPC title

• B64C1/18 Primary

  Floors · CPC title

• C22F1/04

  of aluminium or alloys based thereon · CPC title

• C22C21/18 Primary

  with zinc · CPC title