Gas turbine engines
US4317646A · kind A · utility
56Cited by
5References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 22, 1980 |
| Grant date | Mar 2, 1982 |
| Priority date | — |
| Expiry date | Feb 22, 2000 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/18
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A device for controlling the clearance between the blade tips of a gas turbine engine turbine rotor and associated segmented shrouds comprises a control ring which is secured to the engine casing by a plurality of dowels. The control ring is supplied with cooling fluid to its hollow interior and is covered with a thermally insulating layer, whereby the rate of movement of the shroud segments can be maintained substantially equal to that of the adjacent turbine rotor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.