Научно-инжиниринговая группа

Компрессорная, вакуумная, холодильная техника и системы транспорта и переработки газа

Создана специалистами кафедры "Компрессорная, вакуумная и холодильная техника" и Научной школы компрессоростроения Санкт-Петербургского политехнического университета Петра Великого

The investigation of absolute flow non-uniform velocity distributions influence at the centrifugal compressor axial radial impeller inlet using numerical calculation methods in ANSYS CFX.

Abstract. Currently, methods of numerical modelling are widely used. They are especially widely used in the design of turbo compressors. For the specific task of designing new flowing parts of a centrifugal compressor, it is not recommended to deviating from the canonical design techniques, but it is preferable to supplement them with numerical methods. This article is devoted to the end two-element stage investigation of a centrifugal compressor with an axial radial impeller, the stage main dimensions were obtained by the method of V.F.  Rice. In order to obtain the necessary pressure characteristics and determine the dependence for the absolute velocity non-uniform distribution at the inlet to the axial radial impeller, the flow path main dimensions were optimized using numerical calculation methods.  The calculation was performed using the SST turbulence model using computational gas dynamics methods in the ANSYS CFX software environment.  Based on the optimization results, five compressor designs and corresponding characteristics were obtained.  The absolute velocity distribution nature at the inlet to the centrifugal compressor axial radial impeller for five flow path variants is investigated.  Empirical dependences are obtained for the deviation at the inlet to the absolute velocity in the hub section axial radial impeller and the absolute velocity deviation at the shroud from the absolute velocity at the average diameter based on the results of a numerical experiment.  Recommendations are made for further absolute velocity distributions investigating at the inlet to the compressor impeller.