TECHNICAL MECHANICS
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UDC 519.6:621.51

Technical mechanics, 2019, 3, 38 - 44

AERODYNAMIC IMPROVEMENT OF CENTRIFUGAL COMPRESSOR STAGE INLET GUIDE VANES

DOI: https://doi.org/10.15407/itm2019.03.038

Kvasha Yu. A., Zinevych N. A., Petrushenko N. V.

Kvasha Yu. A.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Zinevych N. A.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Petrushenko N. V.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      This work is devoted to the aerodynamic improvement of elements of centrifugal compressor stages, which is topical because of their use in compressors of modern gas turbine engines. The aim of this work is to construct a technique for aerodynamic improvement of centrifugal compressor stage inlet guide vanes based on a numerical simulation of 3D turbulent gas flows and to verify its operability. The technique features: varying the 3D shape of an inlet guide vane using a parameter variable along the vane, formulating quality criteria as the mean integral values of the impeller power characteristics of the stage under consideration, and searching for an advisable inlet guide vane shape by scanning the variable range at points that form a uniformly distributed sequence. The basic method is a numerical simulation of 3D turbulent gas flows on the basis of the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. By the example of the inlet guide vanes of a centrifugal compressor stage, it was shown by computation that the proposed technique does improve the impeller power characteristics even in the case of a relatively small number of uniformly distributed points. This conclusion was verified by a subsequent calculation of the impeller power characteristics on a finer grid. On the whole, it was shown that varying the inlet guide vane shape has a pronounced effect on the impeller compression ratio and the operating range of the airflow rate, while leaving the impeller adiabatic efficiency almost unaffected. The results obtained are intended to be used in the aerodynamic optimization of elements of aircraft gas turbine engine centrifugal stages.
     

aerodynamic improvement, centrifugal compressor stage, inlet guide vanes, numerical simulation, power characteristics

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DOI: https://doi.org/10.15407/itm2019.03.038

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