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航空喷气发动机公司正在为NASA刘易斯研究中心实施一项液氧/碳氢燃料技术的研究计划,目的是研究在1,000和2,000磅/吋~2(绝)之间的燃烧室压力下,液氧/RP-1煤油的点火和燃烧特性。试验了几种不同的发动机結构。可更换组件包括:具有双股自击和预先雾化三股撞击喷嘴的高、低压喷注器;冷却和非冷却的声谐振器;以及长度在11和15吋之间的石墨燃烧室、再生冷却燃烧室和量热室。为了保证点火,设计并研制了高压液氧/RP-1煤油点火器。该试验计划除了对两种喷注器方案在各种推进剂混合比下确定能量的释放效率和燃烧室的热流外,还提供了横向声振与输送系统耦合的稳定性数据,以便同分析模型进行比较。
Jet Engine Company is conducting a research program for liquid oxygen / hydrocarbon fuel technology at NASA’s Lewis Research Center to study the effect of liquid oxygen / carbon monoxide at combustion chamber pressures between 1,000 and 2,000 psi, RP-1 kerosene ignition and combustion characteristics. Several different engine configurations were tested. Replaceable components include: high and low pressure injector with double self-impact and pre-atomized triple-impact impingement nozzles; cooled and non-cooled acoustic resonator; and graphite combustor with length between 11 and 15 inches, regenerative cooling Combustion chamber and calorimeter chamber. In order to ensure ignition, a high-pressure liquid oxygen / RP-1 kerosene igniter was designed and developed. In addition to determining the energy release efficiency and heat flow in the combustor at various propellant mixing ratios for both injector schemes, the pilot program provides stability data coupled to the transversal vibrillation and delivery system to provide the same data as the analytical model Compare.