ラジアルタービン羽根車内の流れの数値解析

概要

論文の詳細を見る
For the further improvement of aerodynamic performance of a radial turbine with the variable nozzle system. which is designed for the application of automotive turbocharger, the clarification for the influence of the setting angle of nozzle vane on the internal flow of the radial turbine is required. However, it is very difficult to perfom the experimental measurements for the internal flow of a radial turbine because of the small size and the high rotational speed of a radial turbine. In this study, the numerical computations were carried out for the flow in the radial turbine model at three inlet flow angles which were estimated from the setting angle of nozzle vane. The computed results revealed that the behaviors of flow in the nozzle region near the turbine inlet and the complex secondary flow and the associated loss generation in the radial turbine were affected by the inlet flow angle.