Conceptual Design of a Turbofan Engine for a Supersonic Business Jet

摘要

In this work, a design for a new turbofan engine intended for a conceptual supersonic business jet expected to enter service in 2025 is presented. Due to the increasing competition in the aircraft industry and the more stringent environmental legislations, the new engine is expected to provide a low fuel burn to increase the chances of commercial success. The objective is to perform a preliminary design of a jet engine, complying with a set of specifications. The conceptual design has mainly been focused on the thermodynamic and aerodynamic design phases. The thermodynamic analysis and optimization have been carried out using the Numerical Propulsion System Simulation (NPSS) code, where the cycle parameters such as fan pressure ratio, overall pressure ratio, turbine inlet temperature and bypass ratio have been optimized for overall efficiency. With the cycle selected, and the fluid properties at the different flow stations known, the component aerodynamic design, sizing and efficiency calculations were performed using MATLAB. Several aspects of the turbomachinery components have been evaluated to assure satisfactory performance. The result is a two spool low bypass axial flow engine of similar dimensions as the reference engine but with increased efficiency. A weighted fuel flow comparison of the two engines at the key operating conditions shows a fuel burn improvement of 11.8% for the optimized design.