Studi Eksperimental Aliran Sekunder Untuk Axial Compressor Cascade Stagger Kuat Dengan Dan Tanpa Tip-clearance: Distribusi Tekanan Statis Pada Permukaan Blade

Abstract

Secondary Flow Experimental Study for Axial Compressor Cascade Strong Stagger With and Without Tip-Clearance: Static Pressure Distribution on Blade Surface. The performance of blade cascade is influenced by thegrowth and boundary layer\u27s separation along blade surface and endwall (casing and hub). The secondary flow whichhappens near hub and casing compressors is three dimentional flow separation phenomenon comes from interactionblade boundary layer with casing and hub boundary layers in the compressor. The secondary flow causes secondarylosses, blockage effect, and turning angle (deflection) distribution along blade span. The result of the research showsthat the increase of the angle of attack reveals lines of constan pressure to be curved forward (upstream) or pressuregives rise to spanwise caused by a strong curl flow. Separation is also increase and cross between two blades. Hence,three dimentional separation region in corner also increase