Keywords
Citation
(1998), "Measuring turbine blade vibration", Aircraft Engineering and Aerospace Technology, Vol. 70 No. 4. https://doi.org/10.1108/aeat.1998.12770dab.020
Publisher
:Emerald Group Publishing Limited
Copyright © 1998, MCB UP Limited
Measuring turbine blade vibration
Measuring turbine blade vibration
Keywords Aircraft, Measurement, Turbines, Vibration
A collaborative research project funded by Wright Laboratory, Wright-Patterson Air Force Base, Ohio, and coordinated by the Ohio Aerospace Institute in Cleveland is aimed at developing a new way to measure gas-turbine engine blade vibration in aircraft. This will help aircraft manufacturers to predict more accurately appropriate maintenance schedules for engines, which will reduce downtime and ensure greater safety.
The technology development team, known as Propulsion Instrumentation Working Group (PIWG), hopes to develop a non-intrusive method to identify potential high-cycle fatigue problems in compressor blades during development testing in ground test facilities. Target goals by the year 2000 include designing, fabricating, prototyping, and bench testing a 24-channel system that incorporates small optical probes and an integrated set of electronic/processing modules.
Participants in the programme are Allied Signal Aerospace, Allison Engine Corp., GE Aircraft Engines, Pratt & Whitney, US Air Force, Wright Laboratory, Arnold Engineering Development Centre and NASA Lewis Research Centre.
For further information contact Wally Rakowski, Ohio Aerospace Institute, 22800 Cedar Point Road, Cleveland, Ohio 44142, USA. Tel: +1 216 962 3126.