US4326833A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method and replacement member for repairing a gas turbine engine blade member
Assignee: General Electric Co
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Filing: 1980-03-19
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Granted: 1982-04-27
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Expires: 2000-03-19
Abstract
Abstract A gas turbine engine air cooled blade member which includes a base, an airfoil and a platform therebetween generally extending beyond the airfoil, the airfoil including leading and trailing edge portions at least one of which has an edge chamber extending longitudinally of the airfoil and extending chordwise into the airfoil toward the other edge to a longitudinally extending chamber wall is repaired by removing from the blade member at least one blade segment which comprises an edge portion, a part of the chamber wall, and a part of the platform connected with and extending from the edge portion and connected with the chamber wall. This provides for each edge portion removed a first alignment and bonding surface on the blade member remaining. Such alignment and body surface is cleaned to remove surface oxides. There is provided for use in such a repair method, as a replacement for the blade segment removed, a replacement member of substantially the same type of material and of a size and shape which matches the removed blade segment. The replacement member includes a second alignment and bonding surface which matches the first alignment and bonding surface of the blade segment which it replaces. Thereafter, the matched alignment and bonding surfaces are placed into registry and the replacement member is metallurgically bonded to the blade member at such surfaces.
Inventors
- 👤 John W. Zelahy
- 👤 Alexander Raeburn, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 04:13
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; B23P6/005; F; F01; F01D; F01D5/00; 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: 6
Claim 1
Independent Claim
238 words
In a method for repairing a gas turbine engine air cooled blade member which includes a base, an airfoil and a platform therebetween generally extending beyond the airfoil, the airfoil projecting longitudinally from the platform and having chordwise spaced leading and trailing edge portions interconnected by concave and convex sidewalls, at least one edge portion having an edge chamber extending longitudinally of the airfoil and extending chordwise into the airfoil toward the other edge portion to a longitudinally extending chamber wall, the steps of: removing from the blade member a blade segment comprising the edge portion, a part of the chamber wall connected with and facing the edge portion, and a part of the platform connected with and extending from the edge portion and connected with the chamber wall to provide a first alignment and bonding surface on the blade member remaining; cleaning the first alignment and bonding surface to remove surface oxides; providing a replacement member of substantially the same type of material and a size and shape which matches the removed blade segment, the replacement member including a chamber wall and a platform wall which together define a second alignment and bonding surface which matches the first alignment and bonding surface; placing the first and second alignment and bonding surfaces into registry at their respective wall and platform surfaces; and then metallurgically bonding the replacement member with the blade member at the locating and bonding surfaces.
Claim 2
Dependent Claim
238 words
In a method for repairing a gas turbine engine air cooled blade member which includes a base, an airfoil and a platform therebetween generally extending beyond the airfoil, the airfoil projecting longitudinally from the platform and having chordwise spaced leading and trailing edge portions interconnected by concave and convex sidewalls, at least one edge portion having an edge chamber extending longitudinally of the airfoil and extending chordwise into the airfoil toward the other edge portion to a longitudinally extending chamber wall, the steps of: removing from the blade member a blade segment comprising the edge portion, a part of the chamber wall connected with and facing the edge portion, and a part of the platform connected with and extending from the edge portion and connected with the chamber wall to provide a first alignment and bonding surface on the blade member remaining; cleaning the first alignment and bonding surface to remove surface oxides; providing a replacement member of substantially the same type of material and a size and shape which matches the removed blade segment, the replacement member including a chamber wall and a platform wall which together define a second alignment and bonding surface which matches the first alignment and bonding surface; placing the first and second alignment and bonding surfaces into registry at their respective wall and platform surfaces; and then metallurgically bonding the replacement member with the blade member at the locating and bonding surfaces.
Claim 3
Dependent Claim
69 words
The method of claim 1 in which: the blade segment is removed to provide on the remaining blade member substantially planar surfaces on the chamber wall and on the platform to provide a first alignment and bonding surface including predominantly intersecting planar surfaces; and the second alignment and bonding surface on the replacement member is provided with predominantly intersecting planar surfaces which match the first alignment and bonding surface.
Claim 4
Dependent Claim
163 words
A replacement member for a segment of a gas turbine engine air cooled blade, the blade including a base, an airfoil and a platform therebetween generally extending beyond the airfoil, the airfoil projecting longitudinally from the platform and having chordwise spaced leading and trailing edge portions interconnected by concave and convex sidewalls, at least one edge portion having an edge chamber extending longitudinally of the airfoil and extending chordwise into the airfoil toward the other edge portion to a longitudinally extending chamber wall, the replacement member comprising: a longitudinal portion including (a) an edge portion; and (b) a part of the chamber wall connected with and facing the edge portions; (c) the edge portion and an interior surface of the chamber wall part facing the edge portion defining walls of the edge chamber; and a foot portion connected with the longitudinal portion and comprising a part of the platform connected with and extending from the edge portion and connected with the edge chamber.
Claim 5
Dependent Claim
163 words
A replacement member for a segment of a gas turbine engine air cooled blade, the blade including a base, an airfoil and a platform therebetween generally extending beyond the airfoil, the airfoil projecting longitudinally from the platform and having chordwise spaced leading and trailing edge portions interconnected by concave and convex sidewalls, at least one edge portion having an edge chamber extending longitudinally of the airfoil and extending chordwise into the airfoil toward the other edge portion to a longitudinally extending chamber wall, the replacement member comprising: a longitudinal portion including (a) an edge portion; and (b) a part of the chamber wall connected with and facing the edge portions; (c) the edge portion and an interior surface of the chamber wall part facing the edge portion defining walls of the edge chamber; and a foot portion connected with the longitudinal portion and comprising a part of the platform connected with and extending from the edge portion and connected with the edge chamber.
Claim 6
Dependent Claim
67 words
The replacement member of claim 3 in which: the part of the chamber wall connected with and facing the edge portion includes an exterior surface which is substantially planar; and the part of the platform of the foot portion includes a surface remote from the longitudinal portion and which is substantially planar and interconnecting with the substantially planar exterior surface of the part of the chamber wall.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-04-26 | 1985-10-26 | 1986-04-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-04-26 | 1989-10-26 | 1990-04-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-04-26 | 1993-10-26 | 1994-04-27 | $7700.00 | Window Closed / Lapsed |