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本文扼要叙述了一个液氧热传导实验研究和液氧冷却燃烧室的试验规划。超临界氧的热传导实验研究是在压力为17～34.5MPa(2460～5000psia),热通量最大为90MW/m~2(55Btu/in~2.s)的条件下进行的。使以前获得的试验数据和最近的试验数据互相关联,从中推导出一个设计公式,该公式能在±30％以内把95％的试验数据关联起来。现已按这种相关式设计了一批供试验用的液氧冷却燃烧室,并投入了生产。为了鉴定液氧冷却燃烧室的设计原理,特制定一个试验规划。试验的目的有两个:一是验证高压液体火箭发动机中的液氧冷却相关式;二是确定液氧冷却剂渗漏所产生的影响。
In this paper, a brief description of a liquid oxygen heat conduction experimental study and liquid oxygen cooled combustion chamber pilot program. Experimental research on the heat conduction of supercritical oxygen is carried out under the condition of pressure of 17 ~ 34.5MPa (2460 ~ 5000psia) and heat flux of maximum of 90MW / m ~ 2 (55Btu / in ~ 2.s). By correlating the previously obtained test data with the most recent test data, a design formula was deduced from which 95% of the test data was correlated within ± 30%. Now according to this kind of related design a number of experimental liquid oxygen cooled combustion chamber, and put into production. In order to identify the design principle of the liquid oxygen cooled combustion chamber, a test plan is formulated. The purpose of the test is twofold: one is to verify the correlation of liquid oxygen and oxygen in high pressure liquid propellant rocket engine; the other is to determine the influence of liquid oxygen and coolant leakage.