Preliminary Introduction to Virtual Prototyping of Jet Engine Components by Means of Aerodynamic Design

Absztrakt

The goal of the present paper is to provide a short introduction about the ongoing research project in conjunction with virtual prototyping of jet engine components. Several sampling phases can be omitted by computational technology and so significant amount of cost, time and capacity can be saved. Although the steps of the presented process are performed for the components belong to different applications, it can be extended and used for certain engine and its parts also. A concentrated parameter distribution-type method has been developed and implemented to analyse the thermodynamic characteristics of a jet engine by considering the expected specification. Mass and energy balance with realistic thermodynamic conditions are applied in the analytical approach. Mean line design of the compressor and turbine unit can be performed, by which the geometrical sizes of the compressor and turbine will be the output of the method following the 3D extension of the blading. Based on the available dimensions, including the other components, the 3D model of the gas turbine can be prepared in a CAD software. Following the verification of the design, CFD analyses can help to crosscheck the differences between the expected and the computed characteristics of the engine. The results of the simulations can be compared with the available measured and/or previously calculated data for validation and verification purposes and conclusions can be drawn about the accuracy and the efficiency of the used analytical and numerical methods. Inverse design method is a preferable tool to increase static pressure rise, the mass flow rate per unit length in the vanned diffuser of the compressor unit. The results of the inverse design method can be verified by a commercial CFD code via specific test case.