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本文以试验的方法评定了液氧/碳氢燃料喷注器的设计对性能和燃烧室传热的影响。对于液氧/丙烷和液氧/乙醇两种推进剂,给出了两种不同类型喷嘴的数据。试验是在室压为200～400磅/英寸~2(绝)和各种不同混合比的条件下进行的。燃料薄膜冷却流量在燃料总流量的0～15%范围内变化。在选择喷注器的设计条件以及分析多喷嘴喷注器的数据时,单个喷嘴燃烧的摄影数据是有意义的。冷流混合与热点火的混合有很大差别。而这种趋向与以前对自燃“可贮存”推进剂所取得的结果很相似。本文介绍的多喷嘴喷注器的数据,可为前面所说的趋向提供定量的证据,并为发动机的应用提供原始的设计资料。这些数据是在 NASA 的合同下获取的,目的在于为先进的、可重复使用的空间运输系统发动机的设计提供数据基础。
This paper evaluates the effect of the design of a liquid oxygen / hydrocarbon fuel injector on performance and heat transfer in a combustion chamber experimentally. For both liquid oxygen / propane and liquid oxygen / ethanol propellants, data for two different types of nozzles are given. The test is carried out at a chamber pressure of 200-400 psi (absolute) and various mixing ratios. The fuel film cooling flow varies from 0 to 15% of the total fuel flow. The shooting data of a single nozzle burning makes sense when choosing the design conditions of an injector and analyzing the data of a multiple nozzle injector. Mixed cold flow mixing and hot ignition are very different. And this trend is very similar to the previous results on spontaneous “storable” propellants. The multi-nozzle injector data presented in this article provide quantitative evidence of the aforementioned trends and provide original design information for engine applications. These data were acquired under NASA contracts to provide a data base for the design of advanced, reusable space transportation system engines.