US3866448A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus for constructing air cooled turbomachinery blading
Assignee: General Electric Co
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Filing: 1974-04-12
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Granted: 1975-02-18
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Expires: 1994-04-12
Abstract
Abstract An improved method of making an air-cooled turbine blade includes the steps of casting a root or dovetail portion and an airfoil section which includes a leading edge, a hollow body portion, and a trailing edge having a plurality of coolant holes formed therein to the minimum practical cast opening size. The blade is then positioned in a fixture which provides a sealed, pressurized chamber around the root portion thereof; and the trailing edge of the blade is deformed to decrease the size of the trailing edge holes. The deformation is limited to the wall cross ties between each pair of holes, and the deformation is stopped when a desired trailing edge coolant efflux is achieved. A blade is thus provided which has wall cross ties which are both thinner and wider than achievable with present state-of-the-art investment casting techniques. Apparatus for performing the trailing edge crimping is also disclosed.
Inventors
- 👤 Ronald E Dennis
- 👤 William D Treece
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 16:48
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/147; B; B21; B21D; B21D53/00; B21D53/78; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49339; Y10T29/49341
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
204 words
Apparatus for forming the trailing edge portion of a turbomachinery blade, which includes an airfoil having a leading edge portion, concave and convex side walls extending from said leading edge portion and forming at least one internal cavity within said airfoil, and a trailing edge portion comprising a first wall extending from said concave side wall and a second wall extending from said convex side wall, said first and second walls being separated by a plurality of solid wall cross ties which form trailing edge coolant passageways therebetween, and a root portion adapted to connect said airfoil portion to a turbomachinery disc, said apparatus comprising: a blade holding fixture including a casing for forming a chamber around the root portion of said blade, means for sealingly engaging said root portion of said blade while permitting fluid flow communication between sAid chamber and the internal cavity of said blade, means for supplying pressurized air to said chamber, and means for measuring the pressure within said chamber, and a blade crimping fixture which receives the airfoil portion of said blade and includes a blade positioning arm for accurately locating and holding said airfoil portions therein and means for crimping the trailing edge portion of said airfoil.
Claim 2
Dependent Claim
204 words
Apparatus for forming the trailing edge portion of a turbomachinery blade, which includes an airfoil having a leading edge portion, concave and convex side walls extending from said leading edge portion and forming at least one internal cavity within said airfoil, and a trailing edge portion comprising a first wall extending from said concave side wall and a second wall extending from said convex side wall, said first and second walls being separated by a plurality of solid wall cross ties which form trailing edge coolant passageways therebetween, and a root portion adapted to connect said airfoil portion to a turbomachinery disc, said apparatus comprising: a blade holding fixture including a casing for forming a chamber around the root portion of said blade, means for sealingly engaging said root portion of said blade while permitting fluid flow communication between sAid chamber and the internal cavity of said blade, means for supplying pressurized air to said chamber, and means for measuring the pressure within said chamber, and a blade crimping fixture which receives the airfoil portion of said blade and includes a blade positioning arm for accurately locating and holding said airfoil portions therein and means for crimping the trailing edge portion of said airfoil.
Claim 3
Dependent Claim
34 words
Apparatus as recited in claim 1 wherein said blade crimping fixture includes an enlarged cavity which surrounds said trailing edge portion of said airfoil when said airfoil is located within said blade crimping fixture.
Claim 4
Dependent Claim
35 words
Apparatus as recited in claim 2 wherein said blade crimping fixture further includes a removable leading edge blade fixture sector which provides a contoured surface adapted to receive the leading edge portion of said airfoil.
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) | 1978-02-17 | 1978-08-19 | 1979-02-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-02-17 | 1982-08-19 | 1983-02-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-02-17 | 1986-08-19 | 1987-02-18 | $7700.00 | Window Closed / Lapsed |