Simulation and Numerical analysis of change effect of tip blade in compressor stall phenomenon

The discussion of numerical simulation of turbo machine 3-dimensional flow is one of topics that welcomed by researchers and craftsman because of development in hardware and numerical algorithms in last decade. Cheapness of numerical methods with its high abilities in frequent change of geometric parameters and flow characteristics leads that using of these, methods give a big help to advancement in research industrial aims and causes to giving speed to development in scientific researchers.Aim of this research is simulation of 3-dimensional flow that passes from rotor blades of an audio pass compressor by using numerical methods. Κ-ε model flow and mess in blades by using CFX methods and near blades by using twisted frame in ANSYS software simulated. At first for validation of model we used rotor 67 of NASA. Simulation results have been done with acceptable accuracy, and then we used geometry of main model. Stall phenomenon that is one of the most destructive situations for compressors is created in audio pass compressors because of shock phenomenon with returned flows of tip of blades that compressor stricken with gas locks and as a result stall created. In this simulation, by change in blade tip in created situation, stall phenomenon has been surveyed.

کلیدواژه ها:

turbine blade ، optimization ، adjoining method ، isentropic revenue