真实安装角偏差影响压气机性能的不确定性量化

In order to study the influence of blade stage angle deviation on compressor performance and stability, a subsonic single rotor axial compressor was taken as the research object and sparse approximation arbitrary polynomial chaos method was used as uncertainty quantification method to evaluate the uncertainty effect of blade stage angle deviation on compressor aerodynamic performance and flow field structure. Results showed that the performance parameters were all monotonically correlated with the stagger angle deviation, and the fluctuation degree of compressor performance decreased with the decline of mass flow rate. The stagger angle deviation changed the incidence angle. Under the condition of large mass flow rate, the fluctuation of the flow field in the blade root area was the largest because the negative incidence angle was the most serious in this area. Under the condition of small mass flow rate, the tip clearance leakage vortex was significantly affected by stagger angle deviation, and the flow loss fluctuation in the blade tip area was the largest. At the same time, because the development direction and expansion degree of tip clearance leakage vortex changed with the stagger angle deviation under near stall condition, the plugging degree of tip area was affected, finally leading to fluctuation of the compressor stability.