Conceptual Design of a 3-shaft Turbofan Engine
During the forthcoming years many new aircrafts such as A350 and B787 are being designed and continually improved. With these new aircrafts and systems, new engines needs to be designed as well, to meet certain requirements such as fuel burn and weight improvement. In this thesis, a baseline engine with technical specifications consistent with a year 2010 EIS has been selected, and the goal was to create a preliminary design of a new engine named AN15 with year entry into service (EIS) 2025 specications. While no mechanical or cost analyses were performed, main emphasis was on thermodynamic and aerodynamic analysis. Literature studies were performed by reading scientific articles combined with books and educational papers. It was very useful and it also let the students know which direction the development of jet engines are going. The thermodynamical analysis was performed in NPSS (Numerical Propulsion System Simulation). A code, written in C++, was produced in order to fit the requirements of a 3-shafted turbofan engine and with the acquired knowledge from the literature studies it was thermodynamically analysed. The thermodynamical analysis included optimizing parameters such as temperatures and pressure ratios to have an engine as efficient as possible. Once the thermodynamical analysis was done, MATLAB was used to write a script which covered the aerodynamical design such as plotting aspects as well as calculations which were available from open literatures. Velocity triangles for compressor and turbine components in the engine was also generated through the MATLAB script. The result was a 3-shafted turbofan jet engine which had almost the same length as the baseline engine, a 21% larger fan diameter and a fuel burn improvement of 11% compared to the baseline engine. Some of the main conclusions were that propulsive efficiency was increased, but also that the development is going towards jet engine designs with lower fuel consumption.
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