Numerical and Experimental Investigation of an Axial Compressor Flow with Tandem Cascade

Basing on a prototype of DCA airfoil and axial displacement overlap of 10% chord, seven kinds of tangential dis- placements are taken to simulate the flow conditions in tandem cascade with numerical methods to select a better geometry with higher performance. The configuration with tangential displacement b/t =0.83 would gain better flow performance than the others. On this basis, two configurations with tangential displacement b/t=0.67 and 0.83 among several configurations are chosen to take into experimental investigations by using TR-PIV system to capture the flow velocity instantaneously. The configuration with b/t=0.83 is observed a better flow field performance than b/t=0.67. Its injection flow in the gap zone is much stronger, wake zone area of the front and rear blade is smaller and the stream flow is more improved. It shows that the flow performance in experimental investigation is quite in the same trend as the numerical results predict.