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.

Issue Section:
Gas Turbines: Education
Topics:
Aircraft, Gas turbines, Modeling, Engines, Compressors, Design, Erosion, Simulation models, Steady state, Turbines, Wear
1.
Ainley, D. G., and Mathieson, G. C. R., 1951, “A Method of Performance Estimation for Axial-Flow Turbines,” British ARC, R&M 2974.
2.
Aker
G. F.
, and
Saravanamuttoo
H. I. H.
,
1989
, “
Predicting Gas Turbine Performance Degradation Due to Compressor Fouling Using Computer Simulation Techniques
,”
ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER
, Vol.
111
, No.
2
, pp.
343
343
.
3.
Batcho, et al., 1986, “Interpretation of Gas Turbine Response Due to Dust Injection,” DNA-TR-86-306, prepared for DNA under contract DNA 001-83-C-0182.
4.
Balje’, O. E., and Binsley, R. L., 1968, “Axial Turbine Performance Evaluation, Part A—Loss Geometry Relationships,” Journal of Engineering Power.
5.
Georgiou, C. C., 1981, “F404-GE-400 Sand Ingestion Test,” Naval Air Propulsion Center Report Number NAPC-PE-62.
6.
Marx, M. M., 1993, “F404-GE-400 Engine 150-Hour Quality Assurance Fighter Accelerated Mission Endurance Test,” Report Number PE-255, Naval Air Warfare Center Aircraft Division, Trenton, NJ.
7.
Muir
D. E.
,
Saravanamuttoo
H. I. H.
, and
Marshall
D. J.
,
1989
, “
Health Monitoring of Variable Geometry Gas Turbines for the Canadian Navy
,”
ASME Journal of Engineering for Power
, Vol.
111
, No.
2
, pp.
244
–
250
.
8.
Mukhtarov, M. Kh., and Kichakin, V. I., 1969, “Procedure for Estimating Flow Section Losses in Axial-Flow Turbines when Calculating Their Characteristics,” Central Scientific Research Institute of Aircraft Engine Construction, Teploenergtika.
9.
Sallee, G. P., 1980, “Performance Deterioration Based on Existing (Historical) Data: JT9D Jet Engine Diagnostic Program,” NASA CR-135448, Pratt & Whitney Aircraft Group, Contract No. NAS3-20632, Cleveland, OH.
10.
Tabakoff, W., 1986, “Compressor Erosion and Performance Deterioration,” ASME Publication FED-Vol. 37, presented at the AIAA/ASME 4th Joint Fluid Mechanics, Plasma Dynamics, and Lasers Conference, Atlanta, GA.
11.
Tabakoff
W.
,
1987
, “
Compressor Erosion and Performance Deterioration
,”
ASME Journal of Turbomachinery
, Vol.
112
, No.
1
, pp.
78
78
.
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