Method of manufacturing a transpiration cooled ceramic blade for a gas turbine
US4376004A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 15, 1980 |
| Grant date | Mar 8, 1983 |
| Priority date | — |
| Expiry date | Oct 15, 2000 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A transpiration cooled ceramic blade for a gas turbine is shown wherein a spar or strut member defining a root portion and an airfoil portion provides the main structural component of the blade. The air foil portion contains longitudinal grooves in the surface in flow communication with an air flow passage in the root portion and a flexible perforated ceramic tape is wrapped around the air foil portion with the perforations therein in registry with the grooves in the core. The flexible ceramic tape and the strut assembly are heated initially to a low temperature to drive off the binder forming the tape and then heated to a relatively high temperature to fuse the ceramic component of the tape together and to the strut to form a unitary blade structure with internal air flow paths and transpiration cooling orifices through the skin.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.