Neno Novakovic P.E. of Collins Aerospace

Over the years, the aircraft turbojet engine has evolved into one of the most intricate multivariable systems, pivotal in human transportation. It serves not only as a thermodynamic power converter but also as a constant arena for technological advancement. Achieving optimal control and addressing diagnostic challenges necessitates a comprehensive understanding of these engines' parameters and performance aspects. Often, critical technical details of jet engines remain elusive, with only limited information available in manufacturer catalogs. The primary challenge lies in calculating and extrapolating vital performance parameters, relying solely on data such as fuel flow, jet exhaust temperature, and turbine rotation speed.

The impetus for this study stemmed from the need to investigate a recurring issue with several turbojet engines experiencing severe failures during operation. The turbine blades suffered extensive damage in each instance due to excessive heat exposure. The initial step in addressing these problems was developing a mathematical model and dynamic analysis of the turbojet engine. A transfer function for the turbojet engine was defined from operational characteristics and experimental test data. This transfer function described the turbine rotation speed as a controlled parameter, with fuel flow as the controlling parameter. Determining total gain and time constant parameters revealed them as nonlinear functions, primarily reliant on the turbojet engine's mechanical characteristics and thermodynamic processes. Subsequent to establishing consistent initial conditions, the simulation results were scrutinized and compared with experimental test data. In terms of dynamic behavior, this study underscores the high fidelity of the presented mathematical model for turbojet engines. The simulation results demonstrated a numeric accuracy exceeding 1.5%, highlighting the model's effectiveness in replicating real-world performance.

Biography:

Mr. Neno Novakovic, a Professional Engineer (P.E.), is a Senior Principal Engineer at Collins Aerospace - Electric Power Systems. Additionally, he holds the role of Vice Chair for the IEEE Aerospace and Electronics Systems (AES-10) Chapter in Seattle, is recognized as an IEEE Senior member, and actively participates as a member and contributor to the SAE A-6A1 Committee. He possesses a Master's degree in Electrical Engineering. He maintains Professional Engineering licenses in both the state of Washington and the province of Ontario, Canada.

With an impressive career spanning over three decades, Mr. Novakovic has garnered extensive expertise in various aspects of aircraft systems, including design, integration, testing, and certification. Early in his career, while employed by the Department of Defense in former Yugoslavia, he was an integral member of the R&D team responsible for developing advanced turbojet engine control and health monitoring systems. In the early nineties, he relocated to Canada, shifting his focus to the realm of Landing Gear Systems design and integration.

In 2009, Mr. Novakovic embarked on a new chapter by joining Collins Aerospace, where he dedicated his talents to developing cutting-edge electrical power systems for prominent commercial and military programs. In recent years, he has concentrated his efforts on optimizing secondary power distribution and pioneering hybrid propulsion concepts. His innovative contributions have granted several U.S. patents and published technical articles in esteemed SAE Aerospace journals. Furthermore, Mr. Novakovic has been honored to present his work at international conferences and seminars, solidifying his reputation as a distinguished figure in the field.

Address:Seattle, Washington, United States