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低速高温燃气流热模拟试验方法和设备

董素君 齐玢 李志杰 樊未军 张荣春 王浚

董素君, 齐玢, 李志杰, 樊未军, 张荣春, 王浚. 低速高温燃气流热模拟试验方法和设备[J]. 航空动力学报, 2012, 27(5): 961-968.
引用本文: 董素君, 齐玢, 李志杰, 樊未军, 张荣春, 王浚. 低速高温燃气流热模拟试验方法和设备[J]. 航空动力学报, 2012, 27(5): 961-968.
DONG Su-jun, QI Bin, LI Zhi-jie, FAN Wei-jun, ZHANG Rong-chun, WANG Jun. Approach and facility for aerodynamic thermal test by lower speed and high-temperature gas flow[J]. Journal of Aerospace Power, 2012, 27(5): 961-968.
Citation: DONG Su-jun, QI Bin, LI Zhi-jie, FAN Wei-jun, ZHANG Rong-chun, WANG Jun. Approach and facility for aerodynamic thermal test by lower speed and high-temperature gas flow[J]. Journal of Aerospace Power, 2012, 27(5): 961-968.

低速高温燃气流热模拟试验方法和设备

基金项目: 国家自然科学基金(11102010)

Approach and facility for aerodynamic thermal test by lower speed and high-temperature gas flow

  • 摘要: 对比分析了两种气流状态参数和两种加热情况下典型前缘部件表面热流密度的相似性,论证了利用亚声速高温燃气流加热方式进行近地空间高超声速飞行工况气动热模拟试验的可行性.针对高超声速飞行器典型钝头锥结构提出“小喷口低速高温燃气流+石英灯”组合热试验方案.通过采用新型高效双腔蒸发管型燃气发生器、新型带保温夹层和耐高温陶瓷内衬的水冷不锈钢高温管道结构,同时引入电加热器预热及燃烧室两路供油方案,使所建低速高温燃气流热试验设备产生燃气流温度达到2100K,φ250mm喷口处平均径向温度分布梯度约3K/mm,具有线性温度控制功能且稳态控制温差约46K,满足24km、马赫数为6典型高超声速飞行器工况驻点区域高温/大热流密度气动热试验要求.

     

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出版历程
  • 收稿日期:  2012-04-01
  • 刊出日期:  2012-05-28

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