超临界RP-3航空煤油喷嘴内部流动与相变特性研究

To explore the flow and phase transition characteristics of supercritical RP-3 in the injector, the pressure distribution along the injector of supercritical RP-3 are measured by using a self-designed simulation test piece of injector contraction channel. Numerical simulation was carried out by using one-dimensional isentropic calculation method. The static pressure distribution of supercritical aviation kerosene RP-3 in the injector shrinkage channel varies with the injection pressure and temperature. By comparing with the model, it is found that without phase transition, the fitting accuracy of the calculated results and the experimental values is relatively high, and the flow parameters of RP-3 in the nozzle can be well predicted, and the static pressure distribution in the nozzle tends to be consistent. When the condensation phase transition occurs, the differences between the calculated results and the experimental values are large, and the injection parameters have a great influence on the static pressure distribution. Through experiments, the flow and phase transition characteristics of supercritical RP-3 in the injector are obtained.