Method for producing a blade for a turbomachine
Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.
1. A method for producing a blade for a turbomachine, wherein the method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at respective platform regions by a friction welding method at a common joint region of the platform regions to form a joint platform, the blade airfoil and the blade root being made of materials which are different from each other.
2. The method of claim 1 , wherein the friction welding method comprises a linear friction welding method.
3. The method of claim 1 , wherein the friction welding method comprises an orbital friction welding method.
4. The method of claim 1 , wherein the blade airfoil is made of a first TiAl alloy.
5. The method of claim 4 , wherein the first TiAl alloy comprises, as further alloying constituent in addition to Ti and Al, one or more of W, Mo, Nb, Co, Hf, Y, Zr, Er, Gd, Si, C.
6. The method as claimed in claim 4 , wherein the blade root is made of a second TiAl alloy which is different from the first TiAl alloy.
7. The method as claimed in claim 6 , wherein the blade root is made of a titanium aluminide.
8. The method of claim 6 , wherein the blade root is produced by providing a body made of the second TiAl alloy, which is then forged, homogenization-annealed and subsequently shaped into the blade root, the blade root being smoothed at least in some regions.
9. The method of claim 1 , wherein at least the blade airfoil is built up by one or more of selective laser melting, selective laser sintering, electron beam melting and laser deposition welding and/or by hot-isostatic pressing of a capsule filled with material powder.
10. The method of claim 1 , wherein at least one of the blade root and the blade airfoil is heat-treated prior to joining.
11. A blade for a turbomachine, wherein the blade comprises a blade airfoil having a first platform region and being made of a first material and a blade root having a second platform region and being made of a second material that is different from the first material, the first platform region of the blade airfoil being joined directly to the second platform region of the blade root by a friction welding method to form a common joint platform.
12. The blade of claim 11 , wherein the blade airfoil is made of a first TiAl alloy.
13. The blade of claim 12 , wherein the first TiAl alloy comprises, as further alloying constituent in addition to Ti and Al, one or more of W, Mo, Nb, Co, Hf, Y, Zr, Er, Gd, Si, C.
14. The blade of claim 12 , wherein the blade root is made of a second TiAl alloy which is different from the first TiAl alloy.
15. The blade of claim 14 , wherein the blade root is made of a titanium aluminide.
16. A turbomachine, in particular an aero engine, wherein the turbomachine comprises the blade of claim 11 .
17. The blade of claim 13 , wherein the first alloy comprises W.
18. The blade of claim 17 , wherein the blade root is made of a titanium aluminide.
19. The method of claim 5 , wherein the first TiAl alloy comprises W.
20. The method of claim 19 , wherein the blade root is made of a titanium aluminide.