Concept and characteristic of integral transonic fan stage

The inlet flow of transonic fan/compressor stator is subsonic. Four groups of single fan stage projects with different aerodynamic load are investigated by comparative numerical analysis. It is considered that as the improvement of aerodynamic load of the transonic fan/compressor, the transonic flow in stator inlet becomes unavoidable. The results also suggest that active flow control gets unnecessary, the existing design methods are capable of diminishing the separated region, and the stator loss produced by transonic flow can be controlled on an acceptable level, unless the inlet Ma>1.33. The explicit conceptions of transonic stator and the integral transonic fan/compressor stage are defined respectively. At least two differences in fan/compressor design between the transonic and the conventional methods can be summarized: the inlet Ma of stator hub is allowed to be higher than 1.0; the diffusion factor of stator hub ought to be limited below 0.53.