Method of applying wear-resistant materials to turbine blades, and turbine blades having wear-resistant materials

• US 6,164,916 A
• Filed: 11/02/1998
• Issued: 12/26/2000
• Est. Priority Date: 11/02/1998
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Martinez-Brandon, Rosalia Marie, White, Raymond Alan, Frost, Aaron Todd, Jones, Andrew Jr.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US09/184,689
• Time in Patent Office: 785 Days
• Field of Search: 416/189, 416/190, 416/191, 416/241 R, 416/500, 415/200, 29/889.1, 29/889.7, 29/527.2, 29/527.4, 29/527.6, 29/530, 29/557, 148/528, 148/525, 228/262.8, 228/248.1, 228/194, 228/175, 228/262.31
• US Class Current: 416/189
• CPC Class Codes: B23K 35/0233 Sheets, foils B23K35/0244 takes precedence
• CPC Class Codes: B23K 35/3046 Co as the principal constituent
• CPC Class Codes: B23P 6/005 using only replacement pieces of a particular form
• CPC Class Codes: C22C 19/07 based on cobalt
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 5/286 Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion F01D5/288 takes precedence
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: Y10S 416/50 Vibration damping features
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49336 Blade making

Abstract

A method of applying a wear-resistant hardface material (alloy) to a portion of a turbine blade, typically a wear surface on a shrouded turbine blade. A thin foil of brazing alloy (which in the preferred embodiment is a nickel-based alloy) is placed over said wear surface, and a hardface alloy of a greater than desired thickness (which in the preferred embodiment is a cobalt-based alloy) is placed thereover, thereby sandwiching the foil therebetween. The wear surface, foil, and hardface material are heated for a period sufficient to melt the foil and cause bonding of the hardface alloy to the wear surface. The hardface material is thereafter machined to bring the wear surface to design tolerances. A turbine blade, and a method of rebuilding a portion of a turbine blade, are also disclosed.

Claims

1. A method of applying a wear-resistant hardface alloy to a portion of a turbine blade, comprising:

placing a thin foil of a brazing alloy over a mating surface of said portion of said turbine blade;

positioning a hardface alloy of a greater-than-desired thickness over said foil, thereby sandwiching the foil between said portion of said turbine blade and said hardface alloy;

heating said portion of said turbine blade, foil, and hardface alloy for a period sufficient to melt said foil and cause bonding of said hardface alloy to said portion of said turbine blade; and

thereafter machining said hardface alloy so as to reduce said greater-than-desired thickness to a desired lesser thickness.

2. The method as claimed in claim 1, wherein said hardface alloy is comprised of a cobalt-based alloy substantially consisting of the following elements, by percent weight:

space="preserve" listing-type="tabular">______________________________________ Carbon .70-1.0 Cr 26-30 Si 1.0 Ni 4-6 Fe 3.0 Vn .75-1.25 B .005-.10 W 18-21 Co Balance ______________________________________

3. The method as claimed in claim 2, wherein said foil is comprised of a nickel-based alloy substantially consisting of the following elements, by percent weight, namely:

space="preserve" listing-type="tabular">______________________________________ Cr 13 Fe 4 Boron 2.8 Si 4. Ni Balance ______________________________________

4. The method as claimed in claim 2, wherein said foil is comprised of a nickel-based alloy substantially consisting of the following elements, by percent weight, namely:

space="preserve" listing-type="tabular">______________________________________ Cr 19 Boron 1.5 Carbon .08 Si 7.3 Ni Balance ______________________________________

5. The method of claim 1, further comprising adding a powdered metallic alloy in a location intermediate said hardface alloy and said portion of said turbine blade.

6. The method as claimed in claim 5, wherein said step of adding a powdered metallic alloy comprises adding a bead of paste braze alloy over at least one exposed joint interface between said hardface alloy and said portion of said turbine blade prior to heating.

7. The method as claimed in claim 5, wherein said powdered metallic alloy is a nickel-based alloy substantially consisting of the following elements, by percent weight, namely:

space="preserve" listing-type="tabular">______________________________________ Co 10 Cr 8.3 Al 5.5 Ti 1.0 Tantalum 3.0 Molybdenum .7 Tungsten 10 Hafnium 1.5 Carbon .14 Boron .015 Ni Balance ______________________________________

8. The method as claimed in claim 5, wherein said powdered metallic alloy is a nickel-based alloy substantially consisting of the following elements, by percent weight, namely:

space="preserve" listing-type="tabular">______________________________________ Co 22 Cr 15 Boron 2.8 Silicon 3.5 Ni Balance ______________________________________

9. The method as claimed in claim 5, wherein said powdered metallic alloy is a nickel-based alloy, comprised of 60% (by weight) of the alloy claimed in claim 7 and 40% (by weight) of the alloy claimed in claim 8.

10. The method as claimed in claim 5, wherein said powdered metallic alloy substantially comprises by weight %:

space="preserve" listing-type="tabular">______________________________________ Ni 17 Cr 19 Tungsten 4 Carbon .4 Boron .8 Silicon 8 Co Balance. ______________________________________

11. The method as claimed in claim 1, further comprising the step, after positioning the hardface alloy over said foil, of tack-welding the hardface alloy one or more localized positions to said portion of the turbine blade, thereby temporarily holding the foil in sandwiched position between said hardface alloy and said portion of said turbine blade.

12. The method as claimed in claim 1, in which the foil is of a thickness within a range of 1to 5 mm.

13. The method as claimed in claim 1, wherein said heating is carried out in a non-oxidizing atmosphere.

14. The method as claimed in claim 3 or 4, wherein said heating is applied over a time interval sufficient to diffuse at least a portion of the boron in said foil away from an interface formed at said mating surface and said hardface alloy.

15. The method as claimed in claim 1, wherein said heating additionally serves as at least a partial heat treatment for the turbine blade so as to permit simultaneous adhesion of said hardface alloy to said portion of said turbine blade and a partial heat treatment of the turbine blade.

16. The method as claimed in claim 1, wherein said portion of said turbine blade comprises a flat surface on a shroud of a shrouded turbine blade, adapted for contact with a corresponding surface on an adjacent turbine blade.

17. The method as claimed in claim 1, further comprising the step of applying pressure to the hardface alloy while heating.

18. A turbine blade having a wear resistant hardface alloy brazed to a portion thereof by the method as claimed in claim 1.

19. A turbine blade having a shroud and having a notch in said shroud, said notch having a wear resistant hardface alloy applied thereto in accordance with the method according to claim 1.

20. A method of rebuilding a portion of a turbine blade to manufacturing tolerances, comprising:

grinding a portion of said turbine blade to form a ground mating surface;

placing a thin foil of brazing alloy over said mating surface;

positioning a hardface material over said foil, thereby sandwiching the foil between said mating surface and said hardface material;

heating said portion of said turbine blade, foil, and hardface alloy so as to melt said brazing alloy and cause bonding of said hardface material to said portion of said turbine blade; and

machining said hardface material when bonded to said portion of said turbine blade so as to reduce said greater-than-desired thickness to a desired lesser thickness.

21. The method of rebuilding a portion of a turbine blade to manufacturing tolerances as claimed in claim 20, wherein said heating is applied over a time interval.

22. The method of rebuilding a portion of a turbine blade as claimed in claim 20, wherein such heating is carried out as part of a heat treatment of the turbine blade.