Using CFD numerical simulation method

the single-passage flowfield of high pressure compressor rotor-12 with different tip clearances were investigated

and the corresponding total pressure ratio and efficiency were analyzed and compared

then a tip clearance value of optimal performance was obtained.The flowfield structure under optimal performance was discussed next.Finally

based on the finite element analysis software——ANSYS

the radial strain of rotor blade and disc

which are under coupled effect of thermal-structure

were estimated.The research results provide good reference for rotor blade tip clearance assembling and control.