The aircraft jet engine is one of the most complex multivariable systems with multiple inputs and multiple outputs. In the event where jet engine technical details are unknown, or only a few of them are known from manufacturer’s catalogues, the challenge becomes how to calculate and extrapolate critical performance parameters based on only fuel flow, jet exhaust temperature and total thrust.
The brief engineering concept of calculation steps presented herein has the goal of identifying unknown turbojet engine parameters and design characteristics based on limited measurements and test data obtained at static conditions and single operating point. The presented numeric algorithm combined with off design parameters calculation, can be used in jet engine health monitoring and fault detection processes.
Neno Novakovic
Mr. Novakovic has more than 30 years of experience in various aircraft systems design, integration, testing, and certification. In 2009, he joined Collins Aerospace (formerly Hamilton Sundstrand), Power & Control division, and since he has been developing electrical power systems for major commercial and military programs. In recent years, his focus has been on secondary power distribution optimization and hybrid propulsion concepts, where he contributed to several U.S. patents and technical publications. His technical articles are published in SAE Aerospace journals and presented at international conferences and seminars. As a licensed professional engineer in Washington state, he is the SAE International frequent contributor and IEEE senior member.