Aerofoil member for a gas turbine engine
US4321010A · kind A · utility
26Cited by
6References
5Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 31, 1979 |
| Grant date | Mar 23, 1982 |
| Priority date | — |
| Expiry date | Jul 31, 1999 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/284
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.