Compressor for jet engine

3D model of 2 stage transsonic axial compressor Inlet diameter = 276mm; Number of stages- 2; Number of blades: R1-23, S1-37, R2-35, S2-53; Tip clearance in CFD analysis - 0.5 mm. DESIGN PARAMETERS (From CFD analysis): pressure ratio = 2.38; massflow = 7 kg/s; isentropic efficiency > 0.83; corrected spool speed = 29200 rpm.