Performance Deterioration Modeling in Aircraft Gas Turbine Engines PUBLIC ACCESS

[+] Author Affiliations
Anthony V. Zaita

Advanced Engineering and Research Associates, Inc., Arlington, VA

Greg Buley

Naval Surface Warfare Center, Carderock Division, West Bethesda, MD

Glen Karlsons

Naval Air Warfare Center Aircraft Division, Patuxent River, Patuxent River, MD

Paper No. 97-GT-278, pp. V004T16A007; 8 pages
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7871-2
  • Copyright © 1997 by ASME


Steady state performance models can be used to evaluate a new engine’s baseline performance. As a gas turbine accumulates operating time in the field, its performance deteriorates due to fouling, erosion and wear. This paper presents the development of a model for predicting the performance deterioration of aircraft gas turbines. The model accounts for rotating component deterioration based on the aircraft mission profiles and environmental conditions, and the engine physical and design characteristics. The methodology uses data correlations combined with a stage stacking technique for the compressor and a tip rub model along with data correlations for the turbine to determine the amount of performance deterioration. The performance deterioration model interfaces with the manufacturer’s baseline engine simulation model in order to create a deteriorated performance model for that engine.

Copyright © 1997 by ASME
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