Aero-engine performance calculation model based on a new algorithm of turbine cooling

For the two commonly used cooling methods, namely film cooling and convective cooling, developed a new calculation model of turbine cooling and realized the new coupling calculation model with the overall performance calculation model of gas turbine engine. Obtained the overall performance calculation model of gas turbine engine, which takes different cooling methods into consideration and is suitable for gas turbine engine with high turbine inlet temperature and a large amount of air cooling flow. The calculation results obtained by the new turbine cooling algorithm were analyzed and compared with that of simple turbine cooling model and test data, which proved the new algorithm feasible for calculation and provided more detailed airflow parameters in turbine components.