环形缝隙进气转静盘腔传热特性数值模拟

A low radius annular gap inlet rotor stator system cavity model was established for the low-pressure turbine cavity structure of a small aviation engine. The heat transfer characteristics in the rotor-stator system cavity were explored and the distribution characteristics of convective heat transfer coefficient on the rotor disk surface were obtained. The influence of flow parameters such as cold air flow rate and rotor speed，as well as structural parameters such as the position of the annular inlet gap radius，the distance between the rotor and stator disks and the height of the outlet gap on the convective heat transfer coefficient were studied. The empirical relation used to solve the average Nusselt number of disks is obtained. The results show that the convective heat transfer coefficient of the rotor stator system cavity with low radius annular gap intake generally exhibits a characteristic of “higher in the low radius region and overall radial decrease”. When the flow parameters are the same，changes in the individual parameters of flow and rotation speed also affect the heat transfer characteristics. The increase in flow rate and rotational speed both enhance the heat transfer inside the disk cavity. The inlet radius and the clearance between the rotor and stator have a significant impact on the heat transfer in the disk cavity， while the change in the outlet clearance has a smaller impact on the heat transfer in the disk cavity.