Aerodynamic design of five stage axial compressor by numerical simulation

The aerodynamic design of five-stage low-pressure axial compressor(LPC) was conducted aimed at the aerodynamic performance need of the components of a mid-power gas turbine. Two main problem, efficiency and stall margin, were considered and the design parameters of 1D, S2 throughflow, blade shape were filtered and optimized. Full 3D numerical simulations were conducted using Numeca software and Denton code and the results show that the aerodynamic performance at design point exceed the design requirements. To satisfy with the requirements of stall margin of low speed operation, 1D experienced statistical numerical method was used to predict the stall margin resulted from adjusting front stage guide blade and research the rule of adjusting to multi-stage simultaneously, these rule can be used to guide aerodynamic experiments of five-stage LPC. A newly designed five- stage LPC that satisfy with indices of aerodynamic performance is presented in this paper and rule of adjusting guide blade for enhancing stall margin can be used to similar multi-stage axial compressors.