| 氢氧烃三组元发动机燃烧室传热、流阻初步分析 |
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| 引用本文： | 祁锋.氢氧烃三组元发动机燃烧室传热、流阻初步分析[J].推进技术,1990,11(5):30-34,68,69. |
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| 作者姓名： | 祁锋 |
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| 作者单位： | 航空航天部11所 |
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| 摘 要： | 本文对几种发动机的冷却作了分析比较,指出使用铜锆合金是高压大热流发动机的必然要求.对大推力氢氧烃三组元试验发动机燃烧室的传热分析表明:热流仅相当于相同推力氢氧双组元发动机的1/3～1/2,热壁温低于800K,完全满足设计要求,但流阻较大,对氢泵不利.
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| 关 键 词： | 多元燃料 火箭发动机 燃烧室 传热 |
THE PRIMARY ANALYSIS ON HEAT TRANSFER AND PRESSURE DROP OF THE THRUST CHAMBER IN HYDROGEN-OXYGEN-HYDROCARBON TRIPROPELLANT ROCKET ENGINE |
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| Qi Feng.THE PRIMARY ANALYSIS ON HEAT TRANSFER AND PRESSURE DROP OF THE THRUST CHAMBER IN HYDROGEN-OXYGEN-HYDROCARBON TRIPROPELLANT ROCKET ENGINE[J].Journal of Propulsion Technology,1990,11(5):30-34,68,69. |
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| Authors: | Qi Feng |
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| Institution: | The 11th Research Insitilute |
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| Abstract: | The heat transfer analysis on several rocket engines has completed in this paper.It is inevitable for copper-zirconium alloy to be used in hight pre- ssure great heat flux rocket engines. After analyzing the hydrogen-oxygen-hydrocarbon tripropellant rocket engine, we recognized that the heat flux is 1/3 to 1/2 that of hydrogen-oxygen propellant rocket engine with the same thrust.The gas-side wall temperatures satisfy completely the design request which are lower than 800K.But the pressure drop is so large as unfavourable to the hydrogen pump. |
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| Keywords: | Multifuel engine Rocket combustion chamber Heat transfer Computation |
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