Turbine blade clearance control system
US5779436A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 7, 1996 |
| Grant date | Jul 14, 1998 |
| Priority date | — |
| Expiry date | Aug 7, 2016 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/24
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on blades and provided abradable structures. The present system controls a radial clearance or an interface or spaced distance between a tip of a blade and a stationary shroud. The system includes an introduction of a cool fluid or a hot fluid flow or a combination of cool fluid and hot fluid into a support case cavity. The flow is controlled by modulating a flow control apparatus and controlling the expansion of a nozzle support case and a stationary shroud relative to the position of the tip of the turbine blade. The system improves efficiency, longevity and operation of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.