A universal blade modeling method based on the virtual constraint boundaries for a controllable channel and loading form

Rethinking the design method for high-performance two-dimensional blade profiles is crucial for the development of advanced aero engines. This study reexamines the blade design process from the channel perspective and proposes a universal blade modeling method for turbomachinery based on virtual constrained boundaries. This method can control the expansion and contraction process and quantify the cascade channel's loading form. Then, a parameterized comparative analysis was performed on the channel of a high subsonic compressor cascade. Our modeling method effectively reproduced the geometric and aerodynamic characteristics of the initial cascade. By optimizing the cascade channel's diffusion angle distribution, our method greatly improved the cascade's deviation angle characteristics. Under the proposed model, the cascade's deviation angle was reduced by 8.30%, but the impact of changes in the distribution of channel diffusion angle on the total pressure loss coefficient was relatively small. Additionally, the blade loading distribution's impact on its aerodynamic performance was explored by changing the loading form coefficient, and it was found that a front-loaded blade distribution greatly improved the cascade performance under a high attack angle. For example, at an attack angle of +6°, the deviation angle and total pressure loss coefficient of front-loaded cascades were reduced by 21.78% and 24.16%, respectively, compared with aft-loaded cascades. This meant that the attack angle region with low cascade loss was greatly enlarged, thus proving the effectiveness of our modeling method and demonstrating its broad industrial application potential.