Development of a Throughflow Method for Aerodynamic Analysis of Highly Loaded Axial Flow Compressors

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In this paper, a novel engineering platform for throughflow analysis based on streamline curvature approach is developed for the research of a 5-stage compressor. It includes several types of improved loss and deviation angle models for the purpose of reflecting the influences of three-dimensional internal flow in highly loaded multistage compressors with higher accuracy. A spanwise mixing model considering viscous shear force with a no-slip condition is applied to improve assessment about the substantial amounts of radial energy and momentum exchange, a shock model accounting for shock geometry changes is also contained to better simulate transonic flow near the tip regions. In order to validate the reliability and robustness of the method, series of test cases including a subsonic compressor P&W 3S1, a transonic rotor NASA Rotor 1B and especially an advanced high pressure core compressor GE E3 HPC have been conducted. Then the computation procedure is applied to the research of a 5-stage compressor which is designed for developing an industry gas turbine. The overall performance and aerodynamic configuration predicted by the procedure both at design- and part-speed conditions are analyzed and compared with experimental results, which show a good agreement. The throughflow method is verified as a reliable and convenient tool for aerodynamic design and performance prediction of modern highly loaded compressors. It is also qualified for further optimization of the 5-stage compressor.