Aerodynamic Design And Performance Study Of Gas Turbine For Driving Turbo Pump Of Liquid Rocket Engine

Turbo-pumps and gas turbines are two important components in liquid rocket engine systems,which are increasingly valued by researchers at home and abroad.And turbines provide power for turbo-pumps.So the geometric design and aerodynamic performance of the turbine greatly determine the operating performance of the turbo-pump.According to the design parameters,this paper uses Concepts NREC software to carry out the turbine blade geometry in one-dimensional design and three-dimensional design.Bezier parameter curve is used to parametrically fit the end wall profile,and the middle arc of the blade to obtain the three-dimensional blade geometry.The result shows that the blade size meets the design requirements.The commercial CFD software NUMECA is adopted to carry out the three-dimensional aerodynamic numerical simulation inside the turbine,and the internal flow filed is analyzed under the design condition.The result shows that the total-to-static efficiency,mass flow rate and pressure ratio obtained by calculation meet the design requirements.In order to more comprehensively predict the aerodynamic performance of the designed turbine under different conditions,this paper analyzes the turbine characteristics of typical small flow rate(40% mass flow rate)and typical large flow rate(120% mass flow rate)to get the performance curve under different flow rates.The static strength of the turbine is calculated and analyzed after obtaining the turbine.Based on the Workbench platform provided by ANSYS software,the unidirectional coupling method is adopted to calculate the strength and check the safety factor.The result shows that the designed turbine blade meets the strength requirements.