RESEARCH PAPERS: Gas Turbines: Education

Performance Deterioration Modeling in Aircraft Gas Turbine Engines

[+] Author and Article Information
A. V. Zaita

Advanced Engineering and Research Associates, Inc., Technology Development Division, 2361 Jefferson Davis Hwy., Suite UL336, Arlington, VA 22202

G. Buley

Naval Surface Warfare Center, Carderock Division, 9500 MacArthur Blvd., West Bethesda, MD 20817-5700

G. Karlsons

Naval Air Warfare Center Aircraft Division, Patuxent River, Propulsion and Power Engineering, 22119 James Road, Mail Stop 3, Patuxent River, MD 20670-5304

J. Eng. Gas Turbines Power 120(2), 344-349 (Apr 01, 1998) (6 pages) doi:10.1115/1.2818128 History: Received July 01, 1997; Online November 19, 2007


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’s 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 © 1998 by The American Society of Mechanical Engineers
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