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5 Conclusions In this thesis a preliminary design of a supersonic jet engine for a conceptual business jet expected to enter service in 2025 has been carried out. The engine was expected to provide better performance than that of the current engine chosen to propel the aircraft. Based on the provided engine requirements, the thermodynamic cycle has been optimized and basic sizing and aerodynamic design of the main components has been performed. The result is a shorter engine of similar diameter with improved efficiency. A weighted fuel flow comparison of the two engines at the key operating points shows a fuel burn improvement of 11,8% for the new engine, improving the economic aspects of operating the aircraft and lowering the emissions for a reduced environmental impact. The design process of a jet engine is a complex process which covers many different disciplines and there is quite often no obvious solution as an improvement of one parameter often comes at the expense of another. A secondary objective of the thesis was to evaluate whether the knowledge obtained from the courses of the aeronautical program at Mälardalen University are sufficient to perform this type of study, and to recommend courses for students who in the future wish to perform a similar work. The authors’ opinion here is that the knowledge obtained is in the lower part of the range of necessary knowledge, but with proper guidance and determination, it’s certainly not an impossible task. To cover all parts of the design process within the limits of the program may not be possible. Courses covering: thermodynamics, mechanics, aerodynamics, mathematical programming, computer aided design, aero-engine technology and general mathematics are recommended. Most of these are available in the current curriculum of the program. A course going deeper in the theory of gas turbine technology, with a greater focus on the turbomachinery components, could however be developed to provide a better starting point for a project like this. To follow the method provided in this thesis, good MATLAB skills are necessary. 5.1 Future work Only the first stages of the conceptual design process have been carried out and some future work is necessary to complete the engine. Further off-design analysis need to be performed, including a turbomachinery analysis at the off design points. Further mechanical design including material selections, weight estimations and stress calculations need to be carried out. A variable geometry inlet and exhaust design may be necessary to assure good performance over the entire flight envelope. 48PDF Image | Conceptual Design of a Supersonic Jet Engine
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