ZHU Hua yun, XV Zhi ming, HU Guo jun, FENG Jun wei, CHEN Jing, REN Sheng

 

(Hangzhou Turbine Power Group Co.,Ltd., Hangzhou 310016,China)

 

 

Abstract: Aiming at the effect of trailing edge thickness on aerodynamic performance of compressor cascade, a method called blending function of exponential was used to enlarge the trailing edge. The trailing edge thickness was changed between 0.1% and 8.0% relative to chord length with constant chord length, maximum thickness, relative position of maximum thickness, radius of leading edge, installation pitch and installation angle. Modeling 2D turbulence model of compressor cascade according to the Baldwin Lomax, and to the wall near the grid was encrypted. Implicit multi grid method was used for accelerating the convergence speed of calculation. The total pressure loss coefficient, attack angle and lift drag were calculated by NUMECA. The results indicate that when trailing edge thickness increases within certain range, the flow turning angle decreases, but lift drag ratio increases and then decreases. The larger the thickness of trailing edge, the higher the trailing edge loss and total pressure loss coefficient, but the stall attack angle is increased.

 

Key words: compressor; trailing edge thickness; aerodynamic performance; numerical analysis