Computational Investigation on Centrifugal Compressor Performance at Various Altitudes
Small gas turbine engines have been considered as a potential and popular mean of propulsion for Unmanned Aerial Vehicles (UAV).With the advantage of high thrust/power-to-weight-ratio from these engines,small aircraft can have larger payload allowance and higher altitude capability.However,at present,these gas turbine engines are not mature enough to perform critical mission for UAV.To be used for such critical mission,these gas turbine engines need a better reliability,efficiency and endurance.The capability of the engine to work efficiently in conditions at different altitude with the variant of air density is a critical factor related to higher operational ceiling.Hence this work aims to present a Computational Fluid Dynamics (CFD) simulation approach focusing on centrifugal compressors which are applied to turbo machines.A computational method is developed for studying the performance of small gas turbine engines over a range of altitude and ambient temperatures under different engine rates,and a centrifugal compressor simulation model is generated by using CFD techniques.Through numerical solutions obtained for different mesh sets the finest mesh of the model was determined.The performance curves obtained by the CFD simulation has been compared with the results obtained from the analytical method.
turbine engines centrifugal compressor CFD simulation altitude
Yu Wang Zhen Luo
School of Electrical, Mechanical and Mechatronic Systems University of Technology, Sydney, NSW 2007
国际会议
重庆
英文
1123-1128
2011-06-23（万方平台首次上网日期，不代表论文的发表时间）