Patent US4214355A successfully refreshed from Google Patents.
US4214355A
Expired / Lapsed
US
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Method for repairing a turbomachinery blade tip
Assignee: General Electric Co
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Filing: 1977-12-21
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Granted: 1980-07-29
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Expires: 1997-12-21
Abstract
Abstract A turbomachinery blade including a hollow interior is provided with an improved tip cap comprising first and second members each made of an alloy of a composition and properties different from the other. The first member, in the form of a closure plate bonded to sidewalls of the hollow body, is of a nickel-base or cobalt-base superalloy casting characterized by high mechanical strength properties at elevated temperatures. The second member is a rib of the shape of and bonded to the first member and is of a cast alloy characterized by the combination of resistance to oxidation, sulfidation and thermal fatigue at elevated temperatures. The second member provides an outer tip extension of the blade.
Inventors
- 👤 John W. Zelahy
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 23:50
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/20; F01D5/005; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49318; Y10T29/49718; Y10T29/49732; Y10T29/49734; Y10T29/49737
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
139 words
In a method for repairing a turbomachinery blade which includes an airfoil-shaped hollow body having sidewalls defining one portion of an internal cavity and an airfoil-shaped tip cap defining the radially outer boundary of said internal cavity, the steps of: removing the tip cap from the blade body; providing an airfoil-shaped closure plate of a first alloy selected from the group consisting of nickel-base and cobalt-base superalloys, and characterized by high mechanical strength properties at elevated temperatures; diffusion bonding the closure plate to the sidewalls; providing a rib member substantially of the airfoil shape of the closure plate and of a second alloy of composition different from that of the first alloy and characterized by resistance to oxidation, sulfidation and thermal fatigue at elevated temperatures; and then, diffusion bonding the rib member to the periphery of the closure plate.
Claim 2
Dependent Claim
139 words
In a method for repairing a turbomachinery blade which includes an airfoil-shaped hollow body having sidewalls defining one portion of an internal cavity and an airfoil-shaped tip cap defining the radially outer boundary of said internal cavity, the steps of: removing the tip cap from the blade body; providing an airfoil-shaped closure plate of a first alloy selected from the group consisting of nickel-base and cobalt-base superalloys, and characterized by high mechanical strength properties at elevated temperatures; diffusion bonding the closure plate to the sidewalls; providing a rib member substantially of the airfoil shape of the closure plate and of a second alloy of composition different from that of the first alloy and characterized by resistance to oxidation, sulfidation and thermal fatigue at elevated temperatures; and then, diffusion bonding the rib member to the periphery of the closure plate.
Claim 3
Dependent Claim
18 words
The method of claim 1 in which the rib member is a casting having a directionally oriented structure.
Claim 4
Dependent Claim
15 words
The method of claim 2 in which the rib member is a single crystal casting.
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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) | 1983-07-29 | 1984-01-28 | 1984-07-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1987-07-29 | 1988-01-28 | 1988-07-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1991-07-29 | 1992-01-28 | 1992-07-29 | $7700.00 | Window Closed / Lapsed |