Turbo machine shroud-to-rotor blade dynamic clearance control
US5601402A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 6, 1986 |
| Grant date | Feb 11, 1997 |
| Priority date | — |
| Expiry date | Jun 6, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/22
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A clearance control arrangement for the rotor blade-to-stator shroud clearance in an aircraft engine or other turbo machine. The disclosed arrangements use large area piston-like structures located circumferential to the turbo machine and capable of operation from pressures developed within the machine. One disclosed arrangement incorporates static adjustment capability that can be disposed to provide symmetrical or asymmetrical clearances. The disclosed clearance control can be used as a fast-acting supplement or in lieu of other clearance control arrangements and is arranged to be actuated upon sensing the onset of rotor-to-stator collision pinch point conditions in the turbo machine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.