發(fā)布時(shí)間：2019-01-21 18:10

【摘要】：為了獲得高低燃溫組合推進(jìn)劑下噴管溫度邊界層的影響規(guī)律,建立了四個(gè)物理模型,通過(guò)使用不同的低燃溫推進(jìn)劑、不同的質(zhì)量分?jǐn)?shù)來(lái)分析低燃溫燃?xì)鈱?duì)噴管溫度邊界層的影響。結(jié)果顯示,在靠近噴管喉襯位置噴入低燃溫燃?xì)鈺r(shí),僅需少量低燃溫推進(jìn)劑就能很好的降低噴管表面邊界層的溫度;而在遠(yuǎn)離噴管喉襯部位時(shí),即使使用較大的質(zhì)量分?jǐn)?shù),噴管邊界層的降溫效果也不明顯。噴管溫度邊界層的降低受低燃溫燃?xì)鉁囟�、質(zhì)量分?jǐn)?shù)、低燃溫燃?xì)膺M(jìn)口位置以及進(jìn)口直徑影響。
[Abstract]:In order to obtain the influence law of the lower nozzle temperature boundary layer of low and low temperature combined propellant, four physical models were established, and different low burning temperature propellants were used. The effect of low temperature gas on the boundary layer of nozzle temperature is analyzed with different mass fraction. The results show that the temperature of the boundary layer on the surface of the nozzle can be reduced very well if only a small amount of low burning temperature propellant is needed when the gas is injected near the nozzle throat liner. The cooling effect of the nozzle boundary layer is not obvious even when the nozzle is far away from the nozzle throat liner even if the mass fraction of the nozzle is high. The decrease of nozzle temperature boundary layer is affected by low temperature gas temperature, mass fraction, inlet position and inlet diameter.
【作者單位】： 中國(guó)航天科技集團(tuán)第四研究院第41研究所;
【分類(lèi)號(hào)】：V435

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1 嚴(yán)建華,邱坤贊,馬增益,李曉東,池涌,岑可法;非等溫邊界層中相間相互作用實(shí)驗(yàn)研究[J];大連理工大學(xué)學(xué)報(bào);2001年S1期

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