Apparatus and method for controlling a blade tip clearance for a compressor
US7654791B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 29, 2006 |
| Grant date | Feb 2, 2010 |
| Priority date | — |
| Expiry date | Jun 1, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/501
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.