Patent US4128928A successfully refreshed from Google Patents.
US4128928A
Expired / Lapsed
US
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Method of forming a curved trailing edge cooling slot
Assignee: General Electric Co
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Filing: 1976-12-29
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Granted: 1978-12-12
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Expires: 1996-12-29
Abstract
Abstract A curved slot is formed between an internal cavity of an airfoil and the trailing edge thereof by temporarily deflecting the airfoil trailing edge portion toward the suction side thereof, forming a straight slot in the trailing edge portion while it is in the deflected position, and releasing the deflecting pressure to allow the trailing edge portion to spring back into an unstressed condition so as to thereby curve the slot within the trailing edge portion. Further curvatures may be effected by subsequent reformation of the trailing edge portion toward the pressure side of the airfoil.
Inventors
- 👤 L. D. Shotts
- 👤 Raymond W. Wisbey
- 👤 Albert W. Sears
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 06:02
CPC Classifications
B; B23; B23P; B23P15/00; B23P15/02; F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/187; F05; F05D; F05D2250/00; F05D2250/70; F05D2250/71; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49339; Y10T29/49341; Y10T29/49995; Y10T408/00; Y10T408/29; Y10T83/00; Y10T83/04; Y10T83/0405; Y10T83/0419; Y10T83/343
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
102 words
An improved method of forming a cooling air slot between an internal cavity of a turbomachinery airfoil and the trailing edge thereof, wherein the improvement comprises the steps of: (a) forming an airfoil to a first shape; (b) deflecting the trailing edge portion of the airfoil toward the suction side thereof; (c) forming a straight slot which extends between the internal cavity and a point in the trailing portion of the airfoil; and (d) forming the airfoil to a final shape by reforming the trailing edge portion thereof toward the pressure side of the airfoil such that said straight slot becomes curved.
Claim 2
Dependent Claim
102 words
An improved method of forming a cooling air slot between an internal cavity of a turbomachinery airfoil and the trailing edge thereof, wherein the improvement comprises the steps of: (a) forming an airfoil to a first shape; (b) deflecting the trailing edge portion of the airfoil toward the suction side thereof; (c) forming a straight slot which extends between the internal cavity and a point in the trailing portion of the airfoil; and (d) forming the airfoil to a final shape by reforming the trailing edge portion thereof toward the pressure side of the airfoil such that said straight slot becomes curved.
Claim 3
Dependent Claim
26 words
An improved method of forming a cooling air slot as set forth in claim 1 wherein said slot emerges on the pressure side of said airfoil.
Claim 4
Dependent Claim
36 words
An improved method of forming a cooling air slot as set forth in claim 1 wherein the step of final shape forming is performed by a plurality of successive reformations with intermittent heat treatment in between.
Claim 5
Dependent Claim
36 words
An improved method of forming a cooling air slot as set forth in claim 1 and including the step of allowing the deflected trailing edge portion to spring back after the forming of a straight slot.
Claim 6
Dependent Claim
89 words
An improved method of forming a cooling air slot between an internal cavity of a turbomachinery airfoil and the trailing edge thereof wherein the improvement comprises the steps of: (a) deflecting the trailing edge portion of the airfoil toward the suction side thereof; (b) forming a straight slot which extends between the internal cavity and a point in the trailing edge of the airfoil; and (c) releasing the deflecting force and allowing said trailing edge portion to spring back to an unstressed condition whereby said straight slot becomes curved.
Claim 7
Dependent Claim
89 words
An improved method of forming a cooling air slot between an internal cavity of a turbomachinery airfoil and the trailing edge thereof wherein the improvement comprises the steps of: (a) deflecting the trailing edge portion of the airfoil toward the suction side thereof; (b) forming a straight slot which extends between the internal cavity and a point in the trailing edge of the airfoil; and (c) releasing the deflecting force and allowing said trailing edge portion to spring back to an unstressed condition whereby said straight slot becomes curved.
Claim 8
Dependent Claim
26 words
An improved method of forming a cooling air slot as set forth in claim 5 wherein said slot emerges on the pressure side of said airfoil.
Claim 9
Dependent Claim
41 words
An improved method of forming a cooling air slot as set forth in claim 5 and including a further step of permanently reforming said trailing edge portion toward the pressure side of the airfoil so as to further curve said slot.
Claim 10
Dependent Claim
35 words
An improved method of forming a cooling air slot as set forth in claim 7 wherein said permanent reformation step is accomplished by a plurality of successive reformations with intermittent heat treatments of the material.
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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) | 1981-12-11 | 1982-06-12 | 1982-12-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-12-11 | 1986-06-12 | 1986-12-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-12-11 | 1990-06-12 | 1990-12-12 | $7700.00 | Window Closed / Lapsed |