US4050133A
Expired / Lapsed
US
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Method of refurbishing turbine vanes and the like
Assignee: Turbine Components Corp
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Filing: 1976-06-07
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Granted: 1977-09-27
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Expires: 1996-06-07
Abstract
Abstract A method for repairing turbine vanes and the like which have become worn or cracked after extended periods of use. The method embraces the steps of applying molten metal containing a predetermined quantity of silicon to the cracks, and overall to the worn or eroded areas of the vane to build up the same beyond its original surface, sintering the vane in a furnace at a temperature of over 2,000° F thereby burning off some of the silicon, allowing the vane to cool, and thereafter placing it in a high pressure furnace and subjecting it simultaneously to heating to a temperature in excess of 2,000° F and a pressure in excess of 15,000 PSI to drive the build-up material into all of the cracks of the vane and simultaneously effect a densification of the material as well as improving the bond to the original eroded surfaces. Thereafter the vane is removed and allowed to cool, and the built-up surface of the vane is ground down so as to restore the dimensions of the piece substantially to those of a new part.
Inventors
- 👤 Salvatore J. Cretella
- 👤 Matthew Bernardo
- 👤 Ralph T. DeMusis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 05:58
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; B23P6/007; B23P15/00; B23P15/04; F; F01; F01D; F01D5/00; F01D5/005; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/4932; Y10T29/49718; Y10T29/49746; Y10T29/49748; Y10T29/4975; Y10T29/49805
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
261 words
The method of refurbishing an airfoil-shaped metal alloy turbine part having a composition containing substantial quantities of cobalt, chromium, tungsten and nickel, with silicon present in an amount less than several percent, comprising the steps of mixing a preparation of an overlay metal alloy comprising substantially the same respective amounts of cobalt, chromium, tungsten and nickel as contained in said turbine part and with silicon present in an amount less than several percent, adding to said preparation an amount of silicon equal to essentially at least ten percent of the silicon content of the preparation, converting said preparation and added silicon into a molten alloy, applying said molten alloy to the eroded surfaces of the airfoil part to build-up the same beyond its original surface, sintering the airfoil part in a furnace at a temperature above 2,000° F and burning off substantially all of the added silicon contained in the molten alloy that was applied to said part such that the resultant overlay alloy has substantially the same composition as the turbine part, removing and cooling the airfoil part, placing the airfoil part in a high pressure furnace, and heating the airfoil part to a temperature above 2,000° F and simultaneously applying thereto a pressure in excess of 15,000 PSI, thereby effecting a densification of the applied overlay alloy and an improved bond of the applied alloy to the eroded airfoil surfaces, removing the airfoil part and cooling the same, and grinding the overlay surface of the airfoil part to restore the dimensions thereof substantially to those of a new part.
Claim 2
Independent Claim
261 words
The method of refurbishing an airfoil-shaped metal alloy turbine part having a composition containing substantial quantities of cobalt, chromium, tungsten and nickel, with silicon present in an amount less than several percent, comprising the steps of mixing a preparation of an overlay metal alloy comprising substantially the same respective amounts of cobalt, chromium, tungsten and nickel as contained in said turbine part and with silicon present in an amount less than several percent, adding to said preparation an amount of silicon equal to essentially at least ten percent of the silicon content of the preparation, converting said preparation and added silicon into a molten alloy, applying said molten alloy to the eroded surfaces of the airfoil part to build-up the same beyond its original surface, sintering the airfoil part in a furnace at a temperature above 2,000° F and burning off substantially all of the added silicon contained in the molten alloy that was applied to said part such that the resultant overlay alloy has substantially the same composition as the turbine part, removing and cooling the airfoil part, placing the airfoil part in a high pressure furnace, and heating the airfoil part to a temperature above 2,000° F and simultaneously applying thereto a pressure in excess of 15,000 PSI, thereby effecting a densification of the applied overlay alloy and an improved bond of the applied alloy to the eroded airfoil surfaces, removing the airfoil part and cooling the same, and grinding the overlay surface of the airfoil part to restore the dimensions thereof substantially to those of a new part.
Claim 3
Dependent Claim
44 words
The method as defined in claim 1, and including the further step of applying a bead of welding material to cracks which exist in the eroded surface of the part so as to fill the same prior to the application of the molten alloy.
Claim 4
Dependent Claim
31 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part with molten metal particles derived from a metal powder.
Claim 5
Dependent Claim
33 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part with molten metal particles derived from a metal alloy feed wire.
Claim 6
Dependent Claim
36 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part in an atmosphere containing argon, with molten metal particles derived from a metal powder.
Claim 7
Dependent Claim
36 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part in an atmosphere containing hydrogen, with molten metal particles derived from a metal powder.
Claim 8
Dependent Claim
36 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part in an atmosphere containing helium, with molten metal particles derived from a metal powder.
Claim 9
Dependent Claim
43 words
The method as defined in claim 1, wherein the step of applying molten alloy to the part comprises plasma spraying the part with molten metal particles derived from a metal alloy feed wire and which have been heated in an atmosphere of oxy-acetylene.
Claim 10
Dependent Claim
47 words
The method as defined in claim 1, wherein the step of grinding the built-up surface of the part comprises removing controlled quantities of concave and convex surfaces of the part in an apparatus having an abrasive belt and a substantially cylindrical drum around which the belt passes.
Claim 11
Dependent Claim
50 words
The method as defined in claim 1, and including the further step of re-cutting a series of generally cylindrical air-ventilating passages in a concave surface of the part, each of said passages being skewed with respect to planes tangent to the concave surface at the locations of the passages, respectively.
Claim 12
Dependent Claim
42 words
The method as defined in claim 10, wherein the step of re-cutting the air-ventilating passages comprises applying a high-tension sparking electrode to the concave surface of the part consecutively at a series of locations corresponding to the desired positions of the passages.
Claim 13
Dependent Claim
48 words
The method as defined in claim 11, wherein the simultaneous applying of heat and pressure is done sufficient magnitude and quantity to force the applied build-up material deeply into cracks in the surface of the part, so as to substantially completely fill any air spaces in said cracks.
Claim 14
Dependent Claim
188 words
The method as defined in claim 1, wherein the step of applying molten alloy to the eroded surfaces of the airfoil part comprises spraying the latter with a molten metal alloy in a gaseous atmosphere, wherein the step of applying simultaneous heat and pressure to the part involves a degree of heat and a magnitude of pressure which are sufficient to force the applied build-up material deeply into cracks in the surface of the part so as to substantially completely eliminate any air spaces in said cracks, wherein the said grinding step comprises removing controlled quantities of metal from the concave and convex surfaces of the part by an abrasive belt and a substantially cylindrical drum around which the belt passes, said method of claim 1 further including the step of re-cutting a series of generally cylindrical air-ventilating passages in the concave surface of the part by applying a high-tension sparking electrode thereto consecutively at a series of locations corresponding to the desired positions of the passages, each of said passages being skewed with respect to planes tangent to the surface at the locations of the passages respectively.
Claim 15
Dependent Claim
46 words
The method as defined in claim 1, and including the further step of adding to the said preparation of claim 1, the ingredients of carbon, manganese, phosphorous, sulfar and iron, and proportioning all the ingredients of the said preparation to produce a Haynes Alloy No. 25.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-09-26 | 1981-03-28 | 1981-09-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-09-26 | 1985-03-28 | 1985-09-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-09-26 | 1989-03-28 | 1989-09-27 | $7700.00 | Window Closed / Lapsed |