Investigation of a centrifugal compressor and study of the area ratio and TIP clearance effects on performance

Abstract

In this research, the centrifugal compressor of a turbocharger is investigated experimentally and numerically.Performance characteristics of the compressor were obtained experimentally by measurements of rotor speed and flow parameters at the inlet and outlet of the compressor. Three dimensional flow field in the impeller and diffuser was analyzed numerically using a full Navier-Stokes program with SST turbulence model. The performance characteristics of the compressor were obtained numerically, which were then compared with the experimental results. The comparison shows good agreement.Furthermore, the effect of area ratio and tip clearance on the performance parameters and flow field was studied numerically. The impeller area ratio was changed by cutting the impeller exit axial width from an initial value of 4.1 mm to a final value of 5.1 mm, resulting in an area ratio from 0.792 to 0.965. For the rotor with exit axial width of 4.6 mm, performance was investigated for tip clearance of 0.0, 0.5 and 1.0 mm. Results of this simulation at design point showed that the compressor pressure ratio peaked at an area ratio of 0.792 while the efficiency peaked at a higher value of area ratio of 0.878. Also the increment of the tip clearance from 0 to 1 mm resulted in 20 percent efficiency decrease.

Aerodynamic Optimization Design of a 150 kW High Performance Supercritical Carbon Dioxide Centrifugal Compressor without a High Speed Requirement

“…The Shear Stress Transport (extended wall function) turbulence model was selected. Some other scholars [19][20][21] have also used the turbulence model in the analysis of centrifugal compressor, and obtained reasonable results. For the impeller inlet, the total temperature was 309.15 K and the total pressure was 7.8 MPa.…”

The influence of flow passage geometry on the performances of a supercritical CO2 centrifugal compressor

“…It not only over comes the lim i ta tions of k-e tur bu lence Shi model to sim u late the wall re gion of low Reynolds num ber, but also over comes the dis ad van tage that the k-w tur bu lence model has a high re quire ment for grid qual ity, so it is ef fi cient and ac cu rate to sim u late tur bu lent flow. Some other schol ars [14][15][16] have also used the tur bu lence model in the anal y sis of cen trif u gal com pres sor, and ob tained rea son able re sults. The nu mer i cal com pu ta tion in this pa per is ac com plished in com mer cial soft ware CFX.…”

Experimental and numerical flow field investigation through two types of radial flow compressor volutes

“…pitch angle c yaw angle r 2 the variance (the average of the squared differences from the mean) Subscript ave arithmetic mean value 1; 2 first and second conditions P1 À P5 the five hole probe pressures r; h; z cylindrical coordinate Y related to yaw angle P related to pitch angle momentum transport equations were resolved using the shearstress transport (SST) model [13]. Working fluid is air and the flow is assumed to be adiabatic.…”