Abstract
We conducted a series of calculations with the models of turbulent viscosity k–e, SST and three variants of three-dimensional unstructured computational grids. For each variant of the computational grid we calculated each of the two models of turbulent viscosity at axial velocity at input from 110 to 150 m/s. Comparison of results of numerical experiments with data of the physical experimental studies revealed that an error of the computational research is 0.3...8.6 %. Results of the study showed that at the first phase of calculation of the stage of an axial compressor one can recommend using the model of turbulent viscosity k–e and the coarse computational grid. To solve the problems on internal aerodynamics of compressors taking into account the flow in the near-border layer and aerodynamic trail, it is expedient to employ the model of turbulent viscosity SST and the fine adaptive grid.
Highlights
Axial compressors are one of the main elements of modern gas-turbine engines
We chose as the object of study a stage of the axial compressor (Fig. 1) that consists of an inlet guide unit (IGU), an impeller (Im) and a guiding device (GD)
The applied 3D model of the stage of an axial compressor with different variants of topology of the computational grid allows defining the parameters of flow when using different models of turbulent viscosity
Summary
Improving the efficiency and cost-effectiveness of gas turbine engines largely depends on solving the problem of improvement of internal aerodynamics of axial compressors [1]. The first direction provides obtaining of reliable methods of aerodynamic design, based on the results of physical modeling of processes in the flow part of axial compressors. The second direction implies receiving reliable methods of aerodynamic design of compressors based on the use of methods of mathematical modeling to ensure obtaining the assigned parameters of compressors without lengthy and labor-consuming adjusting operations. Solving the direct problem provides obtaining reliable methods of aerodynamic design of compressors in order to receive the assigned parameters. Solution of the inverse problem implies development of computational methods, obtaining and analyzing the characteristics of compressors by the known geometry of the flow part. When employing a numerical experiment, one of the key issues is a substantiated choice of the model of turbulent viscosity and the topology of computational grid
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