Method for manufacturing turbomachine components, blank and final component

Patent metadata

Field	Value
Publication number	US-10760153-B2
Application number	US-201615557400-A
Country	US
Kind code	B2
Filing date	Mar 4, 2016
Priority date	Mar 12, 2015
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

The manufacture of a metal turbomachine part, comprising steps consisting of melting a titanium-aluminium intermetallic compound by plasma torch in a ring mould, extracting therefrom an ingot, as cast, in a state cooled from molten, cutting the ingot into at least one blank with an external shape that is simpler than the more complex one of said part to be manufactured, and machining the blank in order to obtain the part with said more complex external shape.

First claim

The invention claimed is:

1. A method for manufacturing a plurality of elongated metal turbomachine parts, the method comprising:
a) completely melting a titanium-aluminium intermetallic alloy, by plasma torch, and keeping it at a homogeneous temperature, then keeping the titanium-aluminium intermetallic alloy molten by plasma torch, in a ring mould,
b) extracting from the ring mould an ingot, as cast, in a state cooled from molten,
c) cutting the ingot into at least one blank,
d) performing at least one of:
dl) heat treating the at least one blank to obtain a duplex microstructure consisting of gamma grains and lamellar grains (alpha 2 /gamma), and
d 2 ) heat treating the at least one blank to prepare the at least one blank for a hot isostatic compacting and then carrying out such a hot isostatic compacting, and

e) machining the at least one blank in order to obtain, from said at least one blank, said plurality of elongated metal turbomachine parts, wherein the plurality of elongated metal turbomachine parts are disposed parallel with respect to each other.

2. The method of claim 1 , wherein said step d) includes performing said steps dl) and d 2 ) so that a TiAl alloy with gamma grains having a composition containing between approximately 47 and 49 percent aluminium (at %) undergoes, at said step d 2 ):
said heat treatment by heating to a temperature of approximately 1038° C. to 1149° C., for a period of approximately 5 to 50 hours,
then said hot isostatic compacting (HIC) at a temperature of between 1185° C. and 1204° C.

3. The method of claim 2 , wherein said hot isostatic compacting of step d 2 ) is followed by another heat treatment at a temperature of between approximately 1018° C. and 1204° C.

4. The method of claim 1 , wherein:
the cut blank produced in step c) has a given external volume A1,
each elongated turbomachine part produced in step e) has a given external volume A2, and
A2/A1 is greater than 0.95.

5. The method of claim 1 , wherein the at least one cut blank produced at step c) represents more than 95% of at least one of the external volume and the mass of the extracted ingot.

6. The method of claim 1 , wherein step b) of obtaining an ingot comprises the obtaining of a cylindrical or polyhedral ingot.

7. The method of claim 1 , wherein, at step b), the extracted ingot has a diameter of less than or equal to 200 mm, or a cross section of less than approximately 32×10 3 mm 2 .

8. The method of claim 1 , wherein the titanium-aluminium intermetallic alloy comprises 48% Al 2% Cr 2% Nb (at %).

9. The method of claim 1 , wherein:
said step d) includes performing said step d 1 ) so that said titanium-aluminium intermetallic alloy has the gamma grains and a composition containing between approximately 47 and 49 percent aluminium (at %), and
heat treating the at least one blank includes:
- performing a first heat treatment by heating the at least one blank to a temperature of approximately 1038° C. to 1149° C., for a period of approximately 5 to 50 hours, and
- performing a second heat treatment by heating the at least one blank to a temperature of between approximately 1018° C. and 1204° C., without hot isostatic compression.

10. The method of claim 1 , wherein:
the cut blank produced in step c) has a given mass Al,
each elongated turbomachine part produced in step e) has a given mass A2, and
A2/A1 is greater than 0.95.

11. The method of claim 1 , wherein at step a) the titanium-aluminium alloy is completely melted in various vessels and refining hearths above each of which are disposed at least one of multiple plasma torches.

12. The method of claim 1 , wherein at step a) a succession of complete meltings of the titanium-aluminium alloy is carried out.

13. The method of claim 1 , wherein the at least one blank cut from the ingot at step c) has a length (L 2 ) of less than 300 mm.

14. The method of claim 1 , wherein the at least one blank cut from the ingot at step c) has a length (L 2 ) between 220 mm and 240 mm.

15. The method of claim 1 , wherein the ingot extracted at step b) has a diameter of less than or equal to 200 mm, or a cross section of less than approximately 32×10 3 mm 2 and the at least one blank cut from the ingot at step c) has a length (L 2 ) of less than 300 mm.

16. A method for manufacturing at least one metal turbomachine part, the method comprising:
a) completely melting a titanium-aluminium intermetallic alloy, by plasma torch, and keeping it at a homogeneous temperature, then keeping the titanium-aluminium intermetallic alloy molten, by plasma torch, in a ring mould,
b) extracting from the ring mould an ingot, as cast, in a state cooled from molten,
c) cutting the ingot into at least one blank,
d) performing at least one of:
dl) heat treating the titanium-aluminium intermetallic alloy to obtain a duplex microstructure consisting of gamma grains and lamellar grains (alpha 2 /gamma), and
d 2 ) heat treating the titanium-aluminium intermetallic alloy to prepare the titanium-aluminium alloy for a hot isostatic compacting and then carrying out such a hot isostatic compacting, and

e) machining the at least one blank in order to obtain, from said at least one blank, said at least one metal turbomachine part.

17. The method of claim 16 , wherein at step a) the titanium-aluminium alloy is completely melted in various vessels and refining hearths above each of which are disposed at least one of multiple plasma torches.

18. The method of claim 16 , wherein at step a) a succession of sftid-complete meltings of the titanium-aluminium alloy is carried out.

19. The method of claim 16 , wherein the at least one blank cut from the ingot at step c) has a length (L 2 ) of less than 300 mm.

20. The method of claim 16 , wherein the at least one blank cut from the ingot at step c) has a length (L 2 ) between 220 mm and 240 mm.

21. The method of claim 16 , wherein the ingot extracted at step b) has a diameter of less than or equal to 200 mm, or a cross section of less than approximately 32×10 3 mm 2 and the at least one blank cut from the ingot at step c) has a length (L 2 ) of less than 300 mm.

22. The method of claim 16 , wherein:
the cut blank produced in step c) has a given external volume A1,
each elongated turbomachine part produced in step e) has a given external volume A2, and
A2/A1 is greater than 0.95.

23. The method of claim 16 , wherein:
the cut blank produced in step c) has a given mass Al,
each elongated turbomachine part produced in step e) has a given mass A2, and
A2/A1 is greater than 0.95.

24. A method for manufacturing at least one metal turbomachine part, comprising steps:
a) melting a titanium-aluminium intermetallic alloy and keeping it at a homogeneous temperature by means of multiple plasma torches, then keeping the titanium-aluminium intermetallic alloy molten by plasma torch in a ring mould,
b) extracting from the ring mould an ingot, as cast, in a state cooled from molten,
c) cutting the ingot into at least one blank having a length of less than 300 mm,
d) performing at least one of:
dl) heat treating the titanium-aluminium intermetallic alloy to obtain a duplex microstructure consisting of gamma grains and lamellar grains (alpha 2 /gamma), and
d 2 ) heat treating the titanium-aluminium intermetallic alloy to prepare the titanium-aluminium intermetallic alloy for a hot isostatic compacting and then carrying out such a hot isostatic compa

Assignees

• Safran Aircraft Engines

Inventors

• Martin Guillaume
• Marcillaud Céline Jeanne
• Mineur-Panigeon Marie

Classifications

• C22F1/183 Primary

  of titanium or alloys based thereon · CPC title

• C22B9/16

  Remelting metals (liquating C22B9/02) · CPC title

• B22D11/10

  Supplying or treating molten metal (B22D41/00 takes precedence) · CPC title

• B22D7/005

  from non-ferrous metals · CPC title

• C22C14/00

  Alloys based on titanium · CPC title