Corner stall control in linear compressor cascade by blended blade and endwall technique based on large eddy simulation
Author:
Affiliation:
1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
2. Institude for Aero Engine, Tsinghua University, Beijing 100084, China
Funder
National Natural Science Foundation of China
National Major Science and Technology Project of China
Beijing Institute of Technology Research Fund Program for Young Scholars
Publisher
AIP Publishing
Subject
Condensed Matter Physics,Fluid Flow and Transfer Processes,Mechanics of Materials,Computational Mechanics,Mechanical Engineering
Link
https://aip.scitation.org/doi/pdf/10.1063/5.0068826
Reference45 articles.
1. Numerical optimization for stator vane settings of multi-stage compressors based on neural networks and genetic algorithms
2. Numerical investigation of transonic axial compressor rotor flows using an improved transition-sensitized turbulence model
3. Rotor boundary layer development in a two-stage compressor
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