Flow pattern formation due to the interdependency of multi-component interactions and their impact on the performance of turbine and exhaust duct of gas turbine

Abstract

Drawing the inspiration from Full Engine Simulation performed by the scientific community, the methodology for performing an integration analysis of single stage turbine with convergent exhaust nozzle of a small gas turbine engine is developed in the present study. Initially, a numerical simulation on exhaust system supported with experimental validation has been discussed. A scope of improvement in the exhaust system study has been identified and these principles are applied to improve the accuracy of prediction of CFD analysis. By taking the confidence from the validation, a 3D steady pressure-based analysis is carried out to understand the flow patterns and aero-thermal properties of the single stage turbine with convergent type nozzle influenced by the integration. The integration resulted in increased specific work output of the turbine and increased the thrust coefficient of the nozzle. Further important outcomes of this study highlight the changes observed in the performance parameters with and without integration. The thermal pattern across the rotor blades from CFD analysis is observed to be in-line with the used blades of the gas turbine engine thereby reinforcing the accuracy of the methodology developed for the integration study.