Abstract
This study designs and optimizes a high-loaded transonic fan stage using a curvature control method. A fan stage with a total pressure ratio of 2.49 and adiabatic efficiency of over 87 % at the design point is obtained after 3D optimizations. The geometric curvature of the blade passage has important driving and adjusting effects on the mainstream and on the flow in the boundary layer. The reasonable optimization of camber line curvature can weaken the radial secondary flow on the blade surface and decrease shock losses effectively. It can also postpone or suppress boundary layer separation by reorganizing aerodynamic load. Hence, secondary flow losses are reduced, and the overall stall margin is expanded. This method features high precision, high operability, and short design cycle, hence providing highloaded fans/compressors with new freedom to improve design ability and offering new possibility to design system development.
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Acknowledgments
This work was supported by the National Natural Science Foundation of China (Grant Number 51506036) and the small/micro enterprises entrepreneurship projects in science and technology of Shenzhen City, China.
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Recommended by Associate Editor Cheolung Cheong
Jieling Li is a master student majoring in Energy and Power Engineering in Harbin Institute of Technology, China. His research direction is aerodynamic design and optimization of high-loaded transonic fans/compressors.
Huanlong Chen, the corresponding author, is a lecturer in HIT, where he received his Ph.D. in School of Energy Science and Engineering in 2009. His research interests include the aerodynamic design and optimization of turbomachinery, the flow diagnoses in turbomachinery with vortex dynamics method, and computational fluid dynamics.
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Li, J., Chen, H., Liu, Y. et al. Aerodynamic design and optimization of a high-loaded axial fan stage using a curvature control method. J Mech Sci Technol 33, 3871–3883 (2019). https://doi.org/10.1007/s12206-019-0731-1
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DOI: https://doi.org/10.1007/s12206-019-0731-1