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首页> 美国政府科技报告 >IGNITION OF HYDROGEN-OXYGEN ROCKET COMBUSTOR WITH CHLORINE TRIFLUORIDE AND TRIETHYLALUMINUM
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IGNITION OF HYDROGEN-OXYGEN ROCKET COMBUSTOR WITH CHLORINE TRIFLUORIDE AND TRIETHYLALUMINUM

机译：氢氧化三氯化铁与三乙基铝的氢氧火箭燃烧器的点火

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Ignition of a nominal-125-pound-thrust cold (200° R) gaseous-hydrogen - liquid-oxygen rocket combustor with chlorine trifluoride (hypergolic with hydrogen) and triethylaluminum (hypergolic with oxygen) resulted in consistently smooth starting transients for a wide range of combustor operating conditions. The combustor exhaust nozzle discharged into air at ambient conditions.nEach starting transient consisted of the following sequence of events:injection of the lead main propellant, injection of the igniter chemical, ignition of these two chemicals, injection of the second main propellant, ignition of the two main propellants, increase in chamber pressure to its terminal value, and cutoff of igniter-chemical flow.nSmooth ignition was obtained with an ignition delay of less than 100 milliseconds for the reaction of the lead propellant with the igniter chemical using approximately 0.5 cubic inch (0.038 lb) of chlorine tri¬fluoride or 1.0 cubic inch (0.031 lb) of triethylaluminum. These quan¬tities of igniter chemical were sufficient to ignite a 20-percent-fuel hydrogen-oxygen mixture with a delay time of less than 15 milliseconds.nTest results indicated that a simple, lightweight chemical ignition system for hydrogen-oxygen rocket engines may be possible.

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