Aero Gas Turbine Flow Loss And Loss Model

The loss mechanism and loss model of the flow in gas turbine were discussed in this thesis. More than ten typical loss models were systematically analyzed and compared. Furthermore, the assumption, mechanism, prediction, performance calculation etc about these loss models were discussed and examined. A streamline curvature program for analyzing the flow condition and performance of axial flow turbine was modified and used to numerically simulate the turbine thermodynamic performance with six of these loss models. A single stage axial flow turbine was used as example to investigate the effects of loss model on the performance prediction of turbine. The performance as well as the pressure loss coefficient versus blade relative height, average loss coefficient versus inlet flow angle and relative pitch were obtained. The calculation results show that performance prediction results of the turbine are greatly different using different loss models due to the difference in basic theory and assumption. The use of loss model should be paid more attention in the turbine design.