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The Institute of Engineering Thermophysics has made progress in the research of new compressor flow control
[ Instrument network instrument research and development ] The new high-performance aero-engine puts high-load design requirements on the compressor, one of the core components. High-load compressor blades are prone to flow separation on the surface, and then lose functional power and cause aerodynamic losses. The losses are mainly blade shape and end wall losses. In the early stage, researchers conducted more research on how to reduce the flow loss of the end wall, but less research on how to reduce the blade loss of high-load compressor. In response to this problem, the research team of the Advanced Gas Turbine Laboratory of the Institute of Engineering Thermophysics, Chinese Academy of Sciences, based on the fact that shark skin flows to the fin structure in nature to reduce flow resistance, and proposed to install a micro-fin structure on the surface of the compressor blade to reduce the aerodynamic loss of the blade. Research ideas.
Researchers use the open source CFD code OpenFOAM to simulate the internal flow of the compressor cascade channel, compare the results of the large eddy simulation with the experimental results of the cascade, and verify the accuracy of the numerical method to be used; install the micro-fin structure on the suction surface of the compressor cascade , To reduce friction resistance. By comparing the compressor blade boundary layer flow resistance, internal turbulent sequence structure and turbulent pulsation characteristics before and after applying the fin structure, the researchers found that the fin structure can reduce the aerodynamic loss caused by attaching the turbulent boundary layer, and the degree of loss can reach More than 20%. The main flow mechanism behind it comes from two aspects: micro-fins can suppress the lateral pulsation of the turbulent boundary layer; the existence of the fin structure makes the position of the turbulent vortex inside the turbulent boundary layer rise in the normal direction of the wall, resulting in turbulent vortex structure and solid wall The contact area is reduced. Currently, researchers are carrying out related cascade wind tunnel experimental measurements.
A series of studies have shown that the micro-fin structure has the potential to reduce the loss of high-load compressor blades, but it is still necessary to study the interaction of the fin structure and the boundary layer transition and how to arrange the fins reasonably in a three-dimensional complex flow environment. .
Relevant research results are titled Physical mechanisms investigation of sharkskin-inspired compressor cascade based on large eddy simulation method and published on ASME Turbomachinery Technical Conference & Exposition 2020. The research was supported by the Postdoctoral Innovative Talent Support Program.