Active control system for gas turbine blade tip clearance
US6401460B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 18, 2000 |
| Grant date | Jun 11, 2002 |
| Priority date | — |
| Expiry date | Aug 18, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/24
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of actively controlling the clearance between the rotating components and the stationary components of a combustion gas turbine engine includes employing an active control system that controls the temperature of bleed air that is delivered to the stationary and rotating components to control the thermal growth thereof and to avoid a pinch point. The active control system includes one or more sensors and controls the operation of heat sources interposed within the air passages that deliver bleed air to the stationary and rotating components. The heat sources supply heat to the bleed air at specified rates responsive to a correction signal to control the thermal growth of the stationary and rotating components and to control the blade tip
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.