The article describes the analysis of the circumferential groove casing treatment in an axial compressor. To analyze the Pressure across the rotor blade of the axial compressor with and without circumferential case grooving, the control volume near the casing is divided into two parts: the control volumes inside and outside the tip gap. The flow mechanisms of stall margin improvement due to casing grooves in NASA Rotor 67 are quantitatively analyzed. Based on the axial distribution of the axial forces, the contribution of groove to the stall margin improvement is assessed. And the grooves that play a major role in stall margin improvement are ascertained. The pressure across the blade with case grooving is little bit higher than the pressure across the blade without case grooving.

Keywords : NASA Rotor 67, Circumferential Groove Casing, Pressure Analysis, Axial Compressor.