Loss characteristic of stator under different rotational speeds in transonic stage environment

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.