Heat treatment of an alloy based on titanium aluminide

1. A method for treating a titanium-aluminide alloy including 40 to 50 percent atomic (at %) aluminium, the method comprising the following steps:

carrying out a centrifugal casting in a permanent mould in order to obtain a semi-finished product, and then

heat treating the semi-finished product at a pressure below 1700×10 5 pascals (Pa) until a microstructure of the alloy comprising gamma grains and/or lamellar grains (alpha2/gamma) is obtained, wherein the heat treating is made between 1045° C. and 1255° C. during 10 to 40 hours.

2. A method for fabricating, without a hot isostatic pressing, a turbine-engine part made from titanium-aluminide alloy including 40 to 50 percent atomic (at %) aluminium, comprising the following steps:

carrying out centrifugal casting in a permanent mould in order to obtain a semi-finished product with a form less complex than that of the finished product,

heat treating the semi-finished product without hot isostatic pressing, at a pressure lower than 1700×10 5 pascals (Pa) until an alloy microstructure comprising gamma grains and/or lamellar grains (alpha2/gamma) is obtained, wherein the heat treating is made between 1045° C. and 1255° C. during 10 to 40 hours, and then

machining the heat-treated semi-finished product to the form of said part.

3. The method according to claim 1 , wherein the step of obtaining the semi-finished product produced by the centrifugal casting comprises casting in said permanent mould filled by the alloy, so that the size of the internal pores of this alloy is reduced after casting compared with what is was before, the mould being filled by the alloy:

with a speed of flow of the alloy in the mould greater than the rate of solidification of the alloy in the mould, and/or

in less than one minute.

4. The method according to claim 1 , wherein said alloy is one of the following alloys: Ti-48AL-2Cr-2Nb, Ti-48AL-2Mn-2Nb, Ti-49Al-1V, Ti-47Al-1mn-2Nb-0.5W-0.5Mo-0.2Si, and Ti-47Al-5nb-1W.

5. The method according to claim 1 , wherein said alloy is TiAl 48-2-2: 48% Al 2% Cr 2% Nb (at %).

6. The method according to claim 1 , wherein the step of obtaining a semi-finished product produced by casting comprises

said centrifugal casting in a metal mould, following by cutting of said cast alloy into parts in accordance with a blank having at least one symmetry plane.

7. The method according to claim 1 , wherein said step of obtaining a semi-finished product produced by casting, which has an axis and, along this axis, a variable external cross section, comprises:

said centrifugal casting in a metal mould, following by cutting of said cast alloy into parts in accordance with a blank having externally no more than one deflection by means of which the cross section of the semi-finished blank increases or decreases, with, along said axis:

cross-sectional maxima of the blank situated at ends thereof, or

a cross-sectional maximum of the blank situated at only one end.

8. The method according to claim 2 , wherein the semi-finished product as cast is heat treated and is then machined directly, without any intermediate dimensional check.

9. The method according to claim 2 , wherein the step of obtaining the semi-finished product produced by casting comprises:

from a casting of said molten alloy, producing a first ingot in this material,

remelting the first ingot in a cooled metal crucible and pouring the first remelted ingot into a centrifuged permanent metal mould in order to obtain a cast remelted ingot, and

removing the cast remelted ingot from the mould and cutting it into semi-finished product, in accordance with said less complex form.

10. The method according to claim 9 , wherein:

producing the first ingot is done by VAR (vacuum arc remelting) or by PAM (plasma arc melting), and

remelting the first ingot is done by VAR SM (skull melting-cold fusion crucible).

11. The method according to claim 1 , wherein the semi-finished product is heat treated by raising it successively:

to a temperature of between 1045° C. and 1145° C., for 5 to 15 hours,

to a temperature of between 1135° C. and 1235° C., for 3 to 10 hours, at a pressure less than that of hot isostatic pressing, and then

to a temperature of between 1155° C. and 1255° C., for 2 to 15 hours, at a pressure less than that of hot isostatic pressing.

12. The method according to claim 1 , wherein the treatment of the alloy is done without hot isostatic pressing.

13. The method according to claim 2 , wherein the machined part is a turbine blade for an aircraft.

14. The method according to claim 1 , wherein the alloy is intended for a turbine blade for an aircraft.

15. The method of claim 3 , wherein the mould is filled with the alloy in 30 seconds.

16. The method of claim 3 , wherein the mould is filled with the alloy in 20 seconds.