COOLING OF HIGH PRESSURE ROCKET THR^JST CHAMBERS WITH LIQUID OXYGEN
COOLING OF HIGH PRESSURE ROCKET THR^JST CHAMBERS WITH LIQUID OXYGEN
复制标题
使用液氧冷却高压火箭 THR^JST 室
DOI：
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
S. Ameduri
中科院分区：
文献类型：
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作者：
M. Arena;F. Amoroso;R. Pecora;S. Ameduri
以氢和氧为推进剂，超临界液氧（LOX）为助燃剂，在4，14和8，174 MN/m ·（b 00和1200 psia）的燃烧室压力下进行了实验。目的是论证和提供以下几个方面的实验数据：（1）液氧通过燃烧室壁面上的小裂纹泄漏到燃烧室的影响。(1)从加热管实验发展的超临界氧传热关联式的验证。四个推力室，喉部直径为0.06 B m（z.B in.）测定了其中三个在4.14 MM/m（b 00 psia）灭菌舱压力下进行循环试验，直至出现裂纹。1例患者接受了13次额外的热循环PS，无明显金属燃烧或窘迫。第四室在b.274MM/ml（100 psia）压力下操作以获得稳态传热数据。壁温测量证实了热传递相关性。
An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen (LOX) a^ the Caotant was conducted at 4,14 and 8,174 MN/m • (b00 and 1200 psia) Chamber prk7sSUre. The ob,iective was to demonstrate and provide experimental data on the followingo (1) The effect of LOX leaking into the com- bustion region through small cracks in the chamber wall. (1) Verification of the supercritical oxygen heat transfer correlation developed from heated tube experiments. Four thrust chambers with throat diameters of 0.06b m (z.b in.) were tested. Thr^e of these were cyclically tested to 4.14 MM/m (b00 psia) chamber pressure until a crack developed. One had 13 additional hot cyc]PS arrumulated with no ap- parent metal burning or distress. The fourth chamber was operated at b.274 MM/m l (1[00 psia) pressure to obtain steady state heat transfer data. Wall temperature measurements confirmed the hoot transfer correlation.