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Engine technology advancements is a continuous prospects that manufacturers strive to maintain and improve to ensure better reliability, fuel efficiency and optimum operational capabilities. Primary performance parameters such as altitude and Mach number define the operational set points for the engine. The main aim of these efforts is to introduce the production of adequate thrust output to allow safe and stable maneuver of operation. Improving the efficiency and minimizing the operation cost via fuel savings is a key factor for a successful turbofan engine. The current study is to take on analyzing the performance of a high bypass ratio turbofan with the use of Akira DGEN 380 engine simulator [1-2]. This engine simulator is a key part of the laboratory within the college of Aeronautics and Engineering at Kent State University, Ohio and is essential in understanding the thermodynamic and aerodynamics properties of engine components. Moreover, the purpose of this project is to examine changes in engine performance under failure of components that impact the operation of the aircraft. This is done by simulating the aircrafts flight path and recording the engine key operating parameters throughout the flight. We are able to deduce the change in performance when we compare these simulations to a normal flight. Conditions such as specified components unexpected failures under a quantified flight path are being investigated to assess the performance of the engine under such operational circumstances. The typical flight duration for a private light jet is about two hours, and this simulation includes modeling a trip from Cleveland, OH to Washington D.C. During this flight, the maximum cruise altitude of twenty-three thousand feet traveling at about two hundred and fifty miles per hour is reached. The operational evaluation of the engine was assessed during this flight path and results pertaining to failure diagnosis based on the engine response obtained from the virtual test bench are presented and discussed.
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