实际进口条件下超声速燃烧室全流场研究

Investigation of Supersonic Combustor Full Flowfield at Actual Combustor Inlet Conditions

关键词:  超声速燃烧室  进气道/隔离段  冷流  风洞试验  数值模拟

Key words:  Supersonic combustor  Inlet/isolator  Cold flow  Wind tunnel test  Numerical simulation

摘要:

针对自行设计的超燃冲压发动机进气道/隔离段+燃烧室一体化模型,进行了燃烧室实际超声速来流条件下的冷态全流场试验研究与数值模拟,获得了模型在不同来流总压和燃烧室出口反压下的流场结构及沿程静压力分布。试验真实模拟了冷流条件下燃烧室实际的进口环境,结果表明:当燃烧室反压系数较低时,激波串在燃烧室扩张段附近形成；当燃烧室反压系数较高时,激波串在燃烧室进口处形成,并且由于凹槽的影响,激波串向燃烧室上壁面偏斜。

Abstract:

Aiming at self-designed scramjet inlet / isolator + combustor integrated model, this paper carried through cold experimental and numerical investigation of supersonic combustor full flowfield under the conditions of the supersonic stream. The flow structure and the static pressure distribution along the airflow of the model under different stream total pressure and exit backpressure has been obtained. The test actually simulated the cold conditions of the entrance environment of the combustor. And the results showed that when the coefficient of the backpressure was lower, the shock train formed near the expansion section of the combustor, By contrast, when the coefficient of the backpressure was higher, the shock train formed in the combustor entrance, and the shock train was squeezed to the top wall of the combustor because of the cavity.