Reviewed the historical development of the supersonic axial flow compressor, and gave an outlook for its future developments and research orientations. According to the internal flow characteristics of the conventional supersonic axial flow compressors, put forward a high load of supersonic axial compressor aerodynamic design principle. A preliminary design verification of the principle has been carried. The 3D viscous numerical simulation results show that, under the tip tangential speed 360m / s, has achieved a stage pressure ratio 2.3 with efficiency 86.5%. In addition, considering the rotor under impulse condition can get the maximum rotor total pressure ratio with high efficiency, a design principle has also been put forward to solve the high entrance Mach number problem of the downstream stator. But the numerical simulation results show that the multi-shock structure does not have any advantages to reduce the stator losses.
A High-Loaded Supersonic Axial Compressor Aerodynamic Design Principle
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Hu, Y, & Wang, S. "A High-Loaded Supersonic Axial Compressor Aerodynamic Design Principle." Proceedings of the ASME 2012 Gas Turbine India Conference. ASME 2012 Gas Turbine India Conference. Mumbai, Maharashtra, India. December 1, 2012. pp. 181-193. ASME. https://doi.org/10.1115/GTINDIA2012-9634
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