Method of making a blade aerofoil for a gas turbine engine
US4434835A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 9, 1982 |
| Grant date | Mar 6, 1984 |
| Priority date | — |
| Expiry date | Mar 9, 2002 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/182
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A method of making at least the aerofoil of a blade for a gas turbine engine in which the cooling air exit passages, whether at the trailing edge or in other parts of the aerofoil, are cast rather than machined subsequently. In the method a disposable piece is formed with holes of the shape of the holes eventually required in the blade aerofoil. The piece is placed in a die and used to define part of the ceramic core required in the casting process, the die being arranged to produce a channel portion interconnecting the otherwise free ends of the parts of the core which will form the passages. The ceramic core thus formed in a lost-wax casting process to form the blade aerofoil, the channel portion being embedded in the shell mould to support the parts which define the passages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.