4 Pages

Effect of forward swept leading edge on a transonic axial compressor rotor stall margin

WithY.F. Shi, H. Wu, M. Li, K. Mao & L.X. Chen

Compressor performance at the peak of the pressure rise characteristic is limited by aerodynamic instabilities, which lead to rotating stall and surge. Rotating stall has harassed the researchers from the onset of axial compressor industry, and it can deteriorate the compressor performance and lead to excessive blade vibration which possibly makes blade broken, so improving the compressor stability is the aim of many researchers in this field. To avoid the rotating stall and improve the stability, it is necessary to firstly reveal the instability mechanism.