Method of repairing a blade of a one-piece bladed disc of a turbomachine and test piece for implementing the method

1. A method of repairing a blade of a one-piece bladed disc of a turbomachine that includes at least one damaged region by electron-beam welding of a patch using an electron-beam welding machine, comprising:

machining the at least one damaged region of the blade to obtain a region to be repaired with a defined profile along a blade cutting line;

welding a first test piece element with the defined profile to a second test piece element with the same material of the patch using the welding machine with preset operating parameters to obtain a start-of-run test piece;

checking the weld quality of the start-of-run test piece based on a predetermined repair acceptance criteria;

welding the patch on to the region to be repaired of the blade using the same electron-beam welding machine without changing the operating parameters thereof; and

reworking the repaired region by machining,

wherein the patch includes a profile along a patch cutting line, the patch cutting line exactly follows the blade cutting line,

wherein a profile of the first test piece element is the same as the defined profile of the blade, and

wherein a profile of the second test piece is the same as the profile of the patch.

2. The method according to claim 1 , wherein the machining of the damaged region includes cutting out a standardized portion that includes the damaged region along the blade cutting line.

3. The method according to claim 2 , wherein the patch cutting line includes a profile corresponding to the defined profile of the cutting line of the blade with a thickness oversize.

4. The method according to claim 3 , wherein the thickness oversize is approximately 1 mm, divided by about 0.5 mm on each side of the cutting line, and a thickness of the blade varies between 0.5 and 6 mm.

5. The method according to claim 1 , wherein the electron beam is slightly offset on the side with the patch during welding of the patch.

6. The method according to claim 1 , wherein at least one heel attached to the patch is provided.

7. The method according to claim 1 , further comprising, after welding the patch on to the blade, welding a third test piece element with the defined profile to a fourth test piece element, with the same material of the patch using the same electron-beam welding machine without changing the operating parameters thereof to obtain an end-of-run test piece; and

checking the quality of the end-of-run test piece,

wherein a profile of the third test piece element is the same as the profile of the defined profile of the blade, and

wherein a profile of the fourth test piece is the same as the profile of the patch.

8. The method according to claim 7 , further comprising determining the parameters of the electron-beam welding machine by the welding a fifth test piece element with the defined profile to a sixth test piece element to obtain a development test piece and testing, by at least one of non-destructive or destructive testing, the development test piece.

9. The method according to claim 8 , the first, third and fifth elements, and the second, fourth and sixth elements of the start-of-run test piece of the end-of-run test piece and the development test piece, respectively, are identical.

10. The method according to claim 8 , wherein the welding of a test piece is performed with means for simulating the mass environment of the blade to simulate the thermal pumping.

11. The method according to claim 1 , further comprising validating the material/machine pair, during which two plates of the material of the blade, with a thickness at least equal to the maximum thickness of the defined profile of the blade, are welded to obtain a test piece for validating the mechanical integrity, and at least cyclic fatigue tests are carried out on the test piece for validating the mechanical integrity.

12. The method according to claim 1 , wherein the at least one region to be repaired is at least one of blade tips, leading edge or trailing edge corners, leading edges or trailing edges of the blade.

13. The method according to claim 1 , wherein the blade includes Ti17.

14. The method according to claim 1 , wherein the turbomachine is a turbojet.

15. The method according to claim 1 , wherein the first test element is from a portion of a forged preform of the one-piece bladed disk such the first test element has the same surface characteristics and metallurgical properties as the blade.

16. The method according to claim 1 , wherein the start-of-run test piece, the blade and the patch include the same material.

17. The method according to claim 4 , wherein the thickness of the blade varies between 0.7 and 3.45 mm.

18. The method according to claim 6 , wherein the welding of the patch on to the region to be repaired of the blade starts on the at least one heel attached to the patch.