Numerical Simulation Of Internal Flow In Gas Turbine Rotating Parts

Gas turbine plays an important role in the field of national defense and industry.In order to further improve its performance,it is necessary to understand the internal flow characteristics of various types of turbomachinery.At present,the research methods of gas turbine internal flow are mainly divided into experimental methods and numerical simulation methods.The numerical simulation method for its hardware requirements is low,can reduce repeated experiment result in high cost advantages has been widely used.Based on the principle of numerical simulation,the flow field solution program is programmed and used to solve the flow field of various turbomachinery.The main research contents of this paper are as follows:1.In this paper,Reynolds average Navier-Stokes equations in partial differential form are used to describe the internal flows in turnarachinery,and q-ω two-way turbulence model is used to realize the closure of the equations.AUSM+-UP scheme was used to discretize convective term and central difference scheme was used to discretize viscous term.LU-SGS implicit method was used to solve the algebraic equations after discretization.A solution program for internal flow in turbomachinery is developed;2.Use this program and NUMECA commercial software to solve the calculation example of NASA Rotor 37 axial compressor to verify the accuracy of the program calculation,and then use this program to calculate a certain type of centrifugal compressor calculation example.The internal flow of these two compressors is studied.The results show that the calculation results of the program can reflect the aerodynamic parameters of the compressor well,and the program can be used to deal with complicated flow problems such as gas flow separation.3.The solution program is applied to the internal flow simulation of a two-stage air-cooled turbine,and the calculation results are compared with ANSYS-CFX to verify the prediction ability of the solution program for turbine internal flow.To NASA for example,certain level of turbine cold test conducted in turbine dynamic and inlet temperature distortion of the unsteady flow to the internal flow field in turbine impact study,as a result of the action of rotating and moving blade surface of a periodic aerodynamic parameters change,the uneven distribution of gas turbine inlet temperature of turbine aerodynamic performance is affected,along the flow direction,imported hot spot gradually developed,It has great influence on heat transfer.