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RESEARCH PAPERS: Symposium Papers: Measurement Methods in Rotating Components of Turbomachinery

Laser-Optical Blade Tip Clearance Measurement System

[+] Author and Article Information
J. P. Barranger

NASA Lewis Research Center, Cleveland, OH 44135

M. J. Ford

Pratt & Whitney Aircraft Group, West Palm Beach, Fla.

J. Eng. Power 103(2), 457-460 (Apr 01, 1981) (4 pages) doi:10.1115/1.3230742 History: Received May 22, 1980; Online November 09, 2009

Abstract

The need for blade tip clearance instrumentation has been intensified recently by advances in technology of gas turbine engines. A new laser-optical measurement system has been developed to measure single blade tip clearances and average blade tip clearances between a rotor and its gas path seal in rotating component rigs and complete engines. The system is applicable to fan, compressor and turbine blade tipe clearance measurements. The engine mounted probe is particularly suitable for operation in the extreme turbine environment. The measurement system consists of an optical subsystem, an electronic subsystem and a computing and graphic terminal. Bench tests and environmental tests were conducted to confirm operation at temperatures, pressures, and vibration levels typically encountered in an operating gas turbine engine.

Copyright © 1981 by ASME
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