The Influence Of Aerodynamic Performance By Using Tip Winglet With Different Width In Rectangular Compressor Cascade

The rapid development of the aviation industry put forward higher requirements to compressor performance, and the tip winglet technology can making a contribution to the improvement of the compressor rectangle cascade aerodynamic performance. In this context, this article has researched the aerodynamic performance of the rectangle compressor cascade with tip winglets under different widths.This paper has studied the aerodynamic performance of the rectangle compressor cascade with different widths tip winglet, by using the combination method of experiment and numerical simulation. The experiment measured the blades’contour plots of static pressure coefficient on casing, streamline of secondary velocity and total pressure loss on outlet section, under different angles of attack, different tip clearances and different tip winglets with different widths. Numerical simulation studied the performance of experimental blades under different angles of attack and the vortex structure inside the cascade flow channel of different experimental blades in detail.The experiment has found that, with the increasing of the angle of attack, the starting position of the static pressure coefficient on casing moving toward the inlet edge, the tip leakage vortex on outlet section being bigger, and the total pressure loss of blade also being bigger. With the tip clearance being larger, the starting position of the static pressure coefficient on casing moving toward the outlet edge, the tip leakage vortex on outlet section being bigger, the passage vortex being smaller even disappears, the total pressure loss of prototype blade also being bigger, and the total pressure loss of PW20blade and SW20blade being lower. With the increasing of the width of tip winglets, the total pressure loss of the blades with suction side tip winglet first being bigger, then being smaller, the total pressure loss of the blades with pressure side tip winglet being little smaller. While in general, the total pressure loss of PW20under the larger tip clearance and the smaller angle of attack was the lowest.The numerical simulation has found that, under the installation of the pressure side tip winglet which width is double the thickness of the blade on prototype blade, the starting position of the lower passage vortex moves toward the back, and weaken the tip leakage vortex, the upper and lower passage vortex, thereby reduce the total pressure loss and improve the aerodynamic performance of blade. Moreover, the performance of PW20blade under different angles of attack is better than the prototype blade.Synthesize the result of experiment and numerical simulation, can be found that, relative to the prototype blade, the blade with wider pressure side tip winglet, its total pressure loss decreases, aerodynamic performance improves more, under the larger tip clearance and different angles of attack.