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Enhancing Fighter Engine Airstarting Capability
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English
Abstract
In addition to designing fighter engines for stall-free idle to maximum power operation and stall recoverability, it is important to give proper emphasis to sub-idle operation for successful starting. This permits the pilot to confidently bring the engine on-line following an inadvertent flameout caused by either the airplane departing the flight envelope or by a fuel interrupt due to a malfunction. Thus reliable and fast airstart capability enhances flight safety especially of single engine airplanes. Flight testing, therefore, is substantially devoted to airstart evaluation. The paper first explains the influence of engine design features on airstarting, particularly the advantages of the low bypass ratio cycle F100-PW-229 (PW229) engine, which is an increased thrust derivative (IPE) of the highly successful F100-PW-220 engine. Enhancing airstarting capability of the PW229 using variable geometry features and digital control flexibility is discussed. The use of an empirical start model in predicting the improvements is illustrated. Also, flight test data of the F16/PW229 airstart characteristics are presented.
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Citation
Khalid, S. and Legore, R., "Enhancing Fighter Engine Airstarting Capability," SAE Technical Paper 911190, 1991, https://doi.org/10.4271/911190.Also In
References
- F16 C/D Flight Manual T.O. TF-16C-1-1
- Childre M. T. McCoy K. D. “Flight Test Experience of the F100-PW-220 Engine in the F16.” A1AA-87-1845
- Davis J. B. Pollak R. R. “Criteria for Optimizing Starting Cycles for High Performance Fighter Engines.” AIAA-83-1127
- Pollak R. R. “Control System Design Considerations for Starting Turbo-Engines During Cold Weather Operation.” the 76th Symposium of the Propulsion and Energetics Panel on “Low Temperature Environment Operations of Turbo Engines (Design and User's Problems)” Brussels, Belgium Oct. 1990
- U. S. Patent 4809500 dated March 7, 1989 “Transient Control System for Gas Turbine Engines,” Roberts W. C. Khalid S. J.
- Khalid S. J. Hearne R. E. “Enhancing Dynamic Model Fidelity for Improved Prediction of Turbofan Engine Transient Performance.” AIAA-80-1083
- Khalid S. J. “Role of Dynamic Simulation in Fighter Engine Design and Development.” AIAA-89-2467
- Khalid S. J. Faherty M. F. “Propulsion System Flight Test Analysis Using Modeling Techniques.” AIAA-90-3288