US4283822A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method of fabricating composite nozzles for water cooled gas turbines
Assignee: General Electric Co
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Filing: 1979-12-26
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Granted: 1981-08-18
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Expires: 1999-12-26
Abstract
Abstract A method of fabricating a composite nozzle for water-cooled, high temperature gas turbines is provided wherein the nozzle comprises a thermally conducting copper core, a top endwall, a bottom endwall, metal tubing through which water may pass embedded in and extending through the core and into the endwalls and a preformed cladding to protect the nozzle against corrosion. The method utilizes hot isostatic pressure to diffusion bond the nozzle components into an assembly and bond the corrosion resistant cladding to the outer surface of the assembly.
Inventors
- 👤 Myron C. Muth
- 👤 William F. Schilling
- 👤 Edwin L. Teaney
- 👤 Leo C. Willmott
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 14:08
CPC Classifications
B; B23; B23P; B23P15/00; B23P15/04; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49339; Y10T29/49341; Y10T29/49343
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
96 words
An improved method of making a water-cooled turbine nozzle comprising the steps of: (a) forming a copper or copper alloy airfoil core having longitudinal holes extending through said core at predetermined locations, and placing a first plurality of cooling tubes in said holes; (b) forming a top endwall having a composite structure comprising a first upper layer of stainless steel and a first lower layer of high thermal conductivity copper consolidated from metal powder, said endwall having a second plurality of cooling tubes embedded in said first lower layer and extending through said first upper layer;
Claim 2
Dependent Claim
96 words
An improved method of making a water-cooled turbine nozzle comprising the steps of: (a) forming a copper or copper alloy airfoil core having longitudinal holes extending through said core at predetermined locations, and placing a first plurality of cooling tubes in said holes; (b) forming a top endwall having a composite structure comprising a first upper layer of stainless steel and a first lower layer of high thermal conductivity copper consolidated from metal powder, said endwall having a second plurality of cooling tubes embedded in said first lower layer and extending through said first upper layer;
Claim 3
Dependent Claim
158 words
(c) forming a bottom endwall having a composite structure comprising a second lower layer of stainless steel and a second upper layer of high thermal conductivity copper consolidated from metal powder, said endwall having a third plurality of cooling tubes embedded in said second upper layer and extending through said second lower layer; (d) preforming a corrosion resistant outer cladding in the shape of a hollow body open at both ends and having substantially the external dimensions of said nozzle; (e) placing the bottom endwall, the airfoil and the top endwall in said hollow cladding body and joining both endwalls and the airfoil together with a plurality of spar rods; (f) welding said spar rods, said cooling tubes and said cladding body to said endwalls to form an assembly; (g) evacuating air from said assembly and sealing under vacuum; (h) diffusion bonding said assembly under hot isostatic pressure; and (i) machining said bonded assembly to the finished product.
Claim 4
Dependent Claim
158 words
(c) forming a bottom endwall having a composite structure comprising a second lower layer of stainless steel and a second upper layer of high thermal conductivity copper consolidated from metal powder, said endwall having a third plurality of cooling tubes embedded in said second upper layer and extending through said second lower layer; (d) preforming a corrosion resistant outer cladding in the shape of a hollow body open at both ends and having substantially the external dimensions of said nozzle; (e) placing the bottom endwall, the airfoil and the top endwall in said hollow cladding body and joining both endwalls and the airfoil together with a plurality of spar rods; (f) welding said spar rods, said cooling tubes and said cladding body to said endwalls to form an assembly; (g) evacuating air from said assembly and sealing under vacuum; (h) diffusion bonding said assembly under hot isostatic pressure; and (i) machining said bonded assembly to the finished product.
Claim 5
Dependent Claim
29 words
The method of claim 1, wherein diffusion bonding occurs at a temperature of about 1500°-1900° F., at a pressure of 1-25 ksi and for a time of 0.5-4 hours.
Claim 6
Dependent Claim
26 words
The method of claim 2, wherein said corrosion resistant cladding is an alloy consisting essentially in weight percent of 50-80% of nickel and 20-50% of chromium.
Claim 7
Dependent Claim
24 words
The method of claim 3, wherein said cladding is an alloy consisting essentially in weight percent of about 50% of nickel and 50% chromium.
Claim 8
Dependent Claim
29 words
The method of claim 2, wherein said diffusion bonding occurs at a temperature of 1800° F., at a pressure of 10 ksi and for a time of 2 hours.
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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) | 1984-08-17 | 1985-02-16 | 1985-08-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-08-17 | 1989-02-16 | 1989-08-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-08-17 | 1993-02-16 | 1993-08-18 | $7700.00 | Window Closed / Lapsed |