To investigate the aerodynamic and loss characteristics of stator in transonic stage environment at different rotational speeds

the characteristics of a transonic single stage compressor at 09 times of design rotational speed was obtained by a method of experimental investigation. Detailed numerical results in the stator passage were obtained in a range from 07 to 11 times of design rotational speed with validated numerical methods. The impact mechanism of rotational speed on the stator flow field structure was explored. The association between flow field structure and loss distribution were analyzed. Two kinds of loss criteria were compared

and their guidance to the blade optimized design was given. The results show that

as the rotational speed grows

the flow field structure in the top region of stator getting worse

which changes little in the middle and hub regions. Vortices and pressure gradient perform as the driving forces in the transportation of lowenergy fluid in the flow passage

resulting in the lowenergy fluid gathering

thereby making up a highenergyloss area.