The wall temperature distribution of the flame tube of the combustion chamber is strongly affected by the combustion,radiation and flow.The interaction of these influential factors forms a coupling system.In this pape...The wall temperature distribution of the flame tube of the combustion chamber is strongly affected by the combustion,radiation and flow.The interaction of these influential factors forms a coupling system.In this paper,a new method,which is different from the previous methods,has been developed for calculating the temperature distribution of the flame tube wall together with the flow field inside and outside the flame tube. In the calculation,the combustion,heat radiation,cooling air film and injection stream mixing inside the flame tube as well as the secondary air flowing outside the flame tube have been simulated.The calculation,in this paper,uses the SIMPLE algorithm,the k -εturbulence model and the auto-adjustable damping method.By using this method,the 3-D temperature distribution of the flame tube wall of the combustion chamber of an aeroengine has been simulated successfully.The calculation results are compared to the experimental data.The error of wall temperature is less than 10%.展开更多
文摘The wall temperature distribution of the flame tube of the combustion chamber is strongly affected by the combustion,radiation and flow.The interaction of these influential factors forms a coupling system.In this paper,a new method,which is different from the previous methods,has been developed for calculating the temperature distribution of the flame tube wall together with the flow field inside and outside the flame tube. In the calculation,the combustion,heat radiation,cooling air film and injection stream mixing inside the flame tube as well as the secondary air flowing outside the flame tube have been simulated.The calculation,in this paper,uses the SIMPLE algorithm,the k -εturbulence model and the auto-adjustable damping method.By using this method,the 3-D temperature distribution of the flame tube wall of the combustion chamber of an aeroengine has been simulated successfully.The calculation results are compared to the experimental data.The error of wall temperature is less than 10%.
