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Advanced Instrumentation Technology for the Integrated-High-Performance-Turbine-Engine-Technology and High-Cycle-Fatigue Programs FREE

[+] Author Affiliations
William A. Stange, Kelly R. Navarra

Propulsion Directorate, Air Force Research Laboratory, Wright-Patterson AFB, OH

Paper No. 98-GT-458, pp. V005T15A034; 6 pages
doi:10.1115/98-GT-458
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7866-8
  • Copyright © 1998 by ASME

abstract

This paper presents an overview of current research efforts aimed at improving turbine-engine structural-instrumentation capabilities. Emphasis is placed on non-intrusive concepts that will be applicable to the advanced engines currently in use, or concepts being developed for initial operational testing shortly after the turn of the century. Technologies to be described include: blade-tip deflection sensors to determine dynamic stress, thermographic phosphors to measure metal temperature, pressure-sensitive paints and air etalons to measure dynamic pressure, and micro-electro-mechanical systems to assess a variety of parameters. Advantages, potential problems and limitations of each system are presented, and an assessment of the applicability of each system to either the Integrated High Performance Turbine Engine Technology or the High Cycle Fatigue initiative is made.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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