Numerical Simulation Of Shock Waves And Interaction Of Shock And Boundary Layer Within Supersonic Cascade

Now the shortage of energy resource make the economic development of manycountries even harder. The steam turbine, gas turbine and aviation engine were widely usedas the most important energy equipment in the Industry sector as aviation, navigation,transportation , power plant and so on.. Supersonic blade was also used in those energyequipment. So the analysis of the supersonic blade floating theory is very important toreduce the supersonic cascade loss (mainly the shock waves loss and the boundary layerloss )and improve the efficiency. This paper is to study a certain kind of supersonic cascade, using the fine economicsoftware to calculate the cascade plane field , the software was made by the Belgiumcompany NUMECA. The control equation are the N-S equation , Baldwin-Lomaxturbulence model. The discrete of equation is finite volume control way to solute directly.Used the multi-grid and remnant polished technique to accelerate the convergence. by theDetailed Numerical simulation of supersonic cascade, I analyzed the develop of shockwaves and the interaction of shack and boundary layer .after the study of such factors aspressure ,mach number and velocity vector I analyzed the influence of the change of pressrate and blade distance to the shock wave and the interaction of the shock wave to theboundary layer, at last I compared the result to the experiment data.