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某型號(hào)火箭發(fā)動(dòng)機(jī)高空模擬試驗(yàn)中擴(kuò)壓器的 數(shù)值計(jì)算與試驗(yàn)比較

Comparison between the numerical simulation and high altitude simulation test for the ejector of a rocket engine

  • 摘要: 文章利用FLUENT軟件對(duì)某型號(hào)液氫/液氧火箭發(fā)動(dòng)機(jī)在高空模擬引射試驗(yàn)中擴(kuò)壓器進(jìn)行數(shù)值計(jì)算，并與試驗(yàn)測(cè)量數(shù)據(jù)進(jìn)行比較。用Visual C#.NET軟件編制了二次喉道擴(kuò)壓器引射過(guò)程計(jì)算程序，將該程序的計(jì)算結(jié)果與FLUENT軟件的數(shù)值計(jì)算結(jié)果進(jìn)行了比較。利用FLUENT軟件對(duì)二次喉道擴(kuò)壓器在不同入口長(zhǎng)度、不同收縮比和長(zhǎng)徑比情況下的流場(chǎng)情況進(jìn)行了計(jì)算，分析了對(duì)發(fā)動(dòng)機(jī)啟動(dòng)的影響；并把數(shù)值計(jì)算結(jié)果同吹風(fēng)試驗(yàn)的數(shù)據(jù)進(jìn)行了比較，結(jié)果表明數(shù)值計(jì)算具有較高的置信度。

     

    Abstract: The numerical simulation of the high altitude simulation test for a liquid hydrogen/liquid oxygen rocket engine was carried out by using FLUENT software, and the results were compared with the measurement data of the test. Visual C#.NET software and FLUENT software were used to calculate the ejection parameters of the secondary throat diffuser, and their numerical calculation results are compared. The flow field of the secondary throat diffuser was obtained by using FLUENT software under various aspect ratios, or contraction ratios or entrance lengths (Xst), and the influence on the engine startup was analyzed. The results show that the numerical simulation method is reliable.

     

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