Design Study Of Compressor And Turbine Components Of A Micro Turbojet Engine

Micro-turbojet engine as the heart of a small aircraft,its performance for the aircraft plays a vital role,because of size effect,to design two key components of micro turbojet,centrifugal compressor and turbine is difficult,its performance directly affects the performance of micro turbojet engine.For the development of some intelligent cruise ammunition,the aerodynamic design of the centrifugal compressor and the axial turbine components is studied in this paper.The main contents are as follows:First,a typical example with test results is used to check the software tools used in the design process to ensure the reliability of the aerodynamic design results.Secondly,according to the overall given index,in order to ensure the rationality and reliability of the main parameters,combining the two products and three one-dimensional design software,the design of the centrifugal compressor is carried out,and the main geometric parameters of the centrifugal comp ressor The impeller shape and three dimensional CFD analysis were designed repeatedly.The geometry of the impeller geometry was optimized for the meridional flow shape,thickness distribution,blade angle distribution and back bending angle.A new pipe diffuser was proposed.And a new pipe diffuser modeling method based on UG software was established,in which the change of cross-sectional area along the flow path was monitored as the key point of the technology.Finally,three-dimensional CFD calculation is used to coupled analysis centrifugal impeller and new pipe diffuser 's performance of the centrifugal compressor,and the final design is obtained based on this repeated manual optimization,and the working characteristic line of the centrifugal compressor is obtained.The aerodynamic design and matching of centrifugal compressor and axial turbine components of high performance micro turbojet engine are completed according to the target.