| Citation: | MA Feng, SHANG Xun, LIU Hanru, et al. Statistics on aerodynamic sensitivities of blade geometric errors for transonic compressor rotor[J]. Journal of Aerospace Power, 2023, 38（10）：2483-2500 doi: 10.13224/j.cnki.jasp.20210644
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In order to study the sensitivity of the aerodynamic performance of a transonic compressor rotor to different types of geometric errors, NASA Rotor 37 was selected as the research object. The non-uniform rational B-splines (NURBS) surface algorithm and genetic algorithm were used to parameterize the three-dimensional blade surface. A total of 26 geometric errors, including the sweeping error and skewing error, were considered and extracted for the 3D rotor blade. 800 samples were generated by uniform Latin hypercube sampling in association with Monte Carlo algorithm. The loss characteristic and flow structure of Rotor 37 were obtained by steady CFD numerical simulation. Spearman rank correlation and expectation curve analysis were used to investigate the nonlinear relationship between geometric deviations and aerodynamic parameters at two typical working conditions. The flow mechanism analysis was carried out on the most sensitive geometric error model of efficiency under different working conditions. Results indicated that leading-edge profile factor of midspan had the greatest negative effects on rotor efficiency; while suction profile factor near shroud was most negatively correlated with pressure ratio at choke point. As for peak efficiency point, suction profile factor of midspan had the most obvious negative influence on rotor efficiency and pressure ratio. Regarding to near stall point, suction profile factor of midspan had great negative correlation with rotor efficiency. Trailing-edge profile factor of midspan was great positively correlated with pressure ratio.
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