Ceramic blade with tip seal
US5653579A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 14, 1995 |
| Grant date | Aug 5, 1997 |
| Priority date | — |
| Expiry date | Nov 14, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/56
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.