Joco 0.1: Conteneur D'application Modulaire A Base Des Agents BDI De La Plateforme Jadex Suivant La Méthodologie O-Mase

摘要

In this research, results of the designed radial inflow turbo-expander with back swept curve blade rotor have been presented. The spiral casing is designed considering constant mean flow velocity and the areas of cross-sections of the spiral casing are decreased gradually by reducing the width of the flow areas fro m inlet to end. The rotor is shrouded to cope up with centrifugal as well as bending load on the vanes of the rotor and avoid energy losses due to the tip clearance. The degree of reaction is selected as 0.25 in contrast to usual value o f 0.5 at design point on the consideration of absolute velocity of air at nozzle exit needs to be higher than the rotor tip speed. The rotor shaft assembly is supported by externally pressured air bearing. The turbine with coupled brake centrifugal compressor, aerostatic radial and thrust bearing and test rig are developed for conducting experiments. The experiments are conducted with compressed cold air by varying mass flow rates and pressure ratios. At the pressure ratio of 1.6 the temperature drop of 12.5oC of flowing air across turbo expander is achieved and 41% total to static efficiency is obtained. The findings of exhaustive experimentation with the developed turbo expander are illustrated in details in this paper