Sealing device for turbine blades of a turbojet engine
US4565492A · kind A · utility
29Cited by
6References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 6, 1984 |
| Grant date | Jan 21, 1986 |
| Priority date | — |
| Expiry date | Jul 6, 2004 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A sealing device is disclosed for maintaining a small positive clearance between packing segments and the turbine blade tips of a turbojet engine. The packing segments are connected to an inner ring which is, in turn, connected to an outer ring, all disposed within the turbojet casing. The coefficient of thermal expansion of the inner ring is greater than that of the outer ring such that, as air is directed onto the structure from the engine compressor, the differential expansion or contraction of the rings serves to move the packing segment in a radial direction to maintain the clearance between them and the turbine blade tips.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.