Patent US4148350A successfully refreshed from Google Patents.
US4148350A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method for manufacturing a thermally high-stressed cooled component
Assignee: MTU Aero Engines AG
•
Filing: 1977-08-03
•
Granted: 1979-04-10
•
Expires: 1997-08-03
Abstract
Abstract A method for manufacturing a thermally highly stressed, cooled component, more particularly, a blade for turbine engines. A component of the above-mentioned type has a central supporting core formed of a solid material and has connected thereto several short, radially outwardly projecting ridges which, in turn, carry an outer shroud concentrically encompassing the supporting core, and which is made of a through-porous material, whereby the supporting core, ribs, and outer shroud are cast in a single piece.
Inventors
- 👤 Axel Rossmann
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 22:12
CPC Classifications
B; B22; B22C; B22C7/00; B22C7/02; F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/182; F01D5/183
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
116 words
Method of manufacturing a thermally highly-stressed, cooled component, comprising the steps of: (a) forming a part core having the shape of an outer shroud of said component and comprising foamed through-porous ceramic material and including inwardly projecting ridges of a compacted ceramic material; (b) forming a complete core corresponding to the final shape of said component using a part core and fusible material in the injection mold; (c) using molding material to make a mold around the complete core; (d) removing said fusible material by melting; (e) casting said component in an evacuated mold formed about the complete core; and (f) removing said ceramic part core from said cast component through application of a chemical medium.
Claim 2
Dependent Claim
116 words
Method of manufacturing a thermally highly-stressed, cooled component, comprising the steps of: (a) forming a part core having the shape of an outer shroud of said component and comprising foamed through-porous ceramic material and including inwardly projecting ridges of a compacted ceramic material; (b) forming a complete core corresponding to the final shape of said component using a part core and fusible material in the injection mold; (c) using molding material to make a mold around the complete core; (d) removing said fusible material by melting; (e) casting said component in an evacuated mold formed about the complete core; and (f) removing said ceramic part core from said cast component through application of a chemical medium.
Claim 3
Dependent Claim
39 words
A method as defined in claim 1 wherein said component is a turbine blade and said part core corresponds to an airfoil of said turbine blade, and said fusible material corresponds to a root member of said turbine blade.
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) | 1982-04-09 | 1982-10-09 | 1983-04-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-04-09 | 1986-10-09 | 1987-04-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-04-09 | 1990-10-09 | 1991-04-10 | $7700.00 | Window Closed / Lapsed |