An aerodynamic design method of S-shaped transition duct between compressor components was studied. Based on the control of wall static pressure gradient of the transition duct

etc

a half-inverse problem design strategy was proposed

and the corresponding design code was developed. To verify the feasibility of the method

a transition duct for axial-centrifugal compressor was designed by the method mentioned above. The result shows that the static pressure distribution on inner wall along with its geometry can be controlled freely by adjusting the inverse design parameters. The designed static pressure distribution on inner wall can be realized through the numerical matching procedure of the outer wall geometry. The design method is practicable since the total pressure recovery coefficient of the axial-symmetric transition duct can be above 0.98 without searching the optimal static pressure gradient distribution on inner wall

when the duct parameters of inlet-height/length ratio is 0.138

and hub-radius-difference/length ratio is 0.485.