. On the aerodynamic optimization of impellers of supersonic compressor stages.
Journal Title: Технічна механіка, Техническая механика, Technical Mechanics - Year 2016, Vol 2, Issue 2
Abstract
The study deals with the pressing problem of diminution in the computer time for an aerodynamic optimization of blade rims of axial compressors when a numerical simulation of the flow based on the full averaged Navier-Stokes equations is used for calculating the end function. The work goal is to verify the serviceability of the authors’ saving procedure of the aerodynamic optimization of impellers of the supersonic compressor stages. The procedure uses reasonably crude computational grids in a numerical simulation of a 3D turbulent air flow in impellers. However, these grids would be selected in order to save the sensitivity of the computational results to variations in the geometric parameters of a blade rim. Criteria of quality are formulated as air flow-averaging values of the power characteristics of an impeller. Finding the optimal geometric parameters of blades uses the points of the uniformly distributed sequences in space of parameters. The Rotor-37 impeller of a supersonic compressor stage has been selected for computations for verifying the serviceability of the procedure. Using the mentioned high-loaded impeller as an example, it is shown that in comparison with the prototype the improved combinations of the variable geometric parameters of impeller blades can be selected by employing a moderate number of the points of the uniformly distributed sequences. The validity of this conclusion is supported by the following calculation of the power characteristics of the reference impeller and optimized one using a detailed computational grid. The results obtained can be employed for the aerodynamic optimization of the geometric parameters of blade rims of compressor stages.
Authors and Affiliations
Yu. Kvasha, N. Zynevich
Keywords
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