Adaptive Myriad Filter for Improved Gas Turbine Condition Monitoring Using Transient Data

Author:

Surender Vellore P.1,Ganguli Ranjan1

Affiliation:

1. Department of Aerospace Engineering, Indian Institute of Science, Bangalore 650012, India

Abstract

The removal of noise and outliers from measurement signals is a major problem in jet engine health monitoring. In this study, we look at the myriad filter as a substitute for the moving average filter that is widely used in the gas turbine industry. The three ideal test signals used in this study are the step signal that simulates a single fault in the gas turbine, while ramp and quadratic signals simulate long term deterioration. Results show that the myriad filter performs better in noise reduction and outlier removal when compared to the moving average filter. Further, an adaptive weighted myriad filter algorithm that adapts to the quality of incoming data is studied. The filters are demonstrated on simulated clean and deteriorated engine data obtained from an acceleration process from idle to maximum thrust condition. This data was obtained from published literature and was simulated using a transient performance prediction code. The deteriorated engine had single component faults in the low pressure turbine and intermediate pressure compressor. The signals are obtained from T2 (IPC total outlet temperature) and T6 (LPT total outlet temperature) engine sensors with their nonrepeatability values that were used as noise levels. The weighted myriad filter shows even greater noise reduction and outlier removal when compared to the sample myriad and a FIR filter in the gas turbine diagnosis. Adaptive filters such as those considered in this study are also useful for online health monitoring, as they can adapt to changes in quality of incoming data.

Publisher

ASME International

Subject

Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering

Reference18 articles.

1. Volponi, A. J., and Urban, L. A., 1992, “Mathematical Methods of Relative Engine Performances Diagnostics,” SAE Trans., Journal of Aerospace Technical Paper 922048, p. 101.

2. Doel, D. L. , 2003, “Interpretation of Weighted-Least-Squares Gas Path Analysis Results,” J. Eng. Gas Turbines Power, 125, pp. 624–633.

3. DePold, H., and Gass, F. D., 1999, “The Application of Expert Systems and Neural Network to Gas Turbine Prognostics and Diagnostics,” J. Eng. Gas Turbines Power, 121, pp. 607–612.

4. Fasching, W. A., and Stricklin, R., 1982, CF6 Jet Engine Diagnostics Program, Final Report 1, NASA/CR-165582.

5. Glenny, D. E., 1988, “Gas Path Analysis and Engine Performance Monitoring in a Chinook Helicopter,” Paper 25 AGARD-CP-448 1, Engine Condition Monitoring Technology and Experience.

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