Abstract: To study the thermal loading of the liquid rocket engine combustion chamber wall，a simple and accurate method to measure the heat flux of the combustion chamber wall was proposed. Combustion chamber transient temperature data in different radial depths were obtained by conducting rocket engine hot-test. Then，a method of processing data，which was based on the separation of variables，was applied to acquiring the heat flux and temperature of the combustion chamber wall. The conclusions of the research are as followed. The method used in this paper can measure the heat flux and the temperature of combustion chamber wall accurately and will not enlarge the error. During the transient process of the engine hot-test，the response of the combustion chamber wall temperature has obvious hysteresis and 5 seconds are not long enough for temperature to reach the steady state. However，the time that wall heat flux required to reach the steady state is about 2 seconds because of the rapid response，and the changing process of the wall heat flux is similar with the changing process of pressure.

Key words: Liquid rocket engine；Combustion chamber；Wall heat flux；Wall temperature；Combustion chamber pressure

摘要： 为了研究液体火箭发动机燃烧室的壁面热载荷，提出了一种简单、准确的燃烧室壁面热流测量方法。通过发动机热试，测得了距燃烧室壁面不同径向深度的瞬态温度数据，采用一种基于分离变量的数据处理方法，最终得到燃烧室壁面热流和壁面温度。研究表明，提出的热流测量方法能够准确获得燃烧室壁面热流和壁面温度且不会放大误差。发动机热试的瞬态过程中，温度的响应存在明显的迟滞性，5s时间不足以使温度达到稳态。而燃烧室壁面热流响应迅速，达到稳态所需时间在2 s左右，且热流的变化规律与燃烧室压力变化规律一致。

关键词: 液体火箭发动机；燃烧室；壁面热流；壁面温度；燃烧室压力