Abstract: A single-injector heat-sink chamber was designed and hot-fire tested for 17 times at chamber pressure from 0.92 MPa to 6.1 MPa,and wall temperature measurement method was used to get the heat flux distributions on the inner wall along with the axial direction of the chamber.The convection heat fluxes were separated from the total heat fluxes to identify the relationship between the convection heat flux and corresponding chamber pressure.Single-injector chamber flows were also simulated with multi-species turbulence N-S equations at higher chamber pressure from 5 MPa to 20 MPa.Chemical reaction was modeled with Arrhenius formulation.Detailed 9 steps chemical mechanism was used to describe the reaction of hydrogen and oxygen.Both the flows structures and heat flux profiles on inner wall were obtained and discussed,and the results of ex-periments and calculations indicated the same trend.

Key words: Liquid propellant rocket engine;Thrust chamber;Thermodynamic cycle;Heat transfer;Experiment;Nu-merical simulation

摘要： 设计了单喷嘴气气喷注器容热式推力室,进行了0.92～6.1 MPa范围内7个燃烧室压力工况,共17次热试车;采用壁面测温方法获得推力室沿轴向方向的内壁热流分布,得到各室压工况下燃烧室内壁热流分布曲线,不同工况的热流曲线显示出相似的分布;并从中分离出对流传热热流,得到对流传热热流与室压的关系。为拓展范围,采用多组分湍流N-S方程描述推力室内燃烧流动,采用6组分9步反应模型来描述氢氧反应,反应速率由Arrhenius公式计算,进行了5～20 MPa更高室压范围内的燃烧内流场的数值模拟,并耦合计算了各工况燃气与室壁之间的传热,获得了与试验相同规律的结果。

关键词: 液体推进剂火箭发动机;推力燃烧室;热力学循环;传热;试验;数值仿真