| In this paper,through numerical calculation and experimental research,the flow rate of kerosene in the regenerating cooling channel of scramjet at the nozzle is systematically and comprehensively studied.The flow characteristics of kerosene at the nozzle under the subcritical pressure of liquid phase,gas-liquid phase,compression flow and supercritical flow are given,and the general rules are given for the fuel supply system and nozzle.The design provides research ideas.In the aspect of numerical calculation,the flow rate and other parameters of ndecane in the two-phase flow state with different diameters of throat are obtained through calculation.The influence of heat flow density,throat diameter and pressure on the above parameters is studied.It is found that the flow rate increases with the increase of throat diameter and pressure,and decreases with the increase of heat flow density.In terms of experiments,the flow characteristics of kerosene in liquid and gasliquid phase at subcritical pressure were studied.The effects of total pressure,back pressure and temperature on the flow at the nozzle were systematically studied.It was found that the flow rate increased with the decrease of back pressure in liquid phase and decreased with the increase of temperature in two-phase.In the aspect of experiment,the flow characteristics of kerosene compression flow and supercritical flow at the nozzle under supercritical pressure were studied.The influence of total pressure and back pressure temperature on the flow at the nozzle was studied.It was found that under supercritical pressure,the flow decreased with the increase of temperature,and the flow increased with the decrease of back pressure. |
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