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亚音速燃烧
相关语句
  subsonic combustion
     In this paper the principle and current condition of study are described that how totransfer subsonic combustion into supersonic combustion in chamber. The experiment shows thevariations of parameters at sections along combustor and the effects of injector location and fuel/airratio on combustion state
     描述了在超音速燃烧室中如何从亚音速燃烧模态转变为超音速燃烧模态的概念和目前的研究状态,并用实验表明改变氢燃料喷射位置和当量比对燃烧状态的影响,以及燃烧室各截面参数的变化规律。
短句来源
     In this paper,a supersonic combustor formed of a segment with constant cross section,a divergent segment and a segment with constant cross section is designed,and do combustion tests with it It is indicated by one dimensional calculation that supersonic combustion or subsonic combustion can be realized as flight speeds with the supersonic combustor formed of a segment with constant cross section,and by different fuel supplied ways,which makes the flight lower limit of Scramjet engine extended up to flight Mach number 3
     本文设计了由等截面段、扩张段和等截面段构成的超音速燃烧室,并进行了燃烧实验。 用一维计算分析实验结果,表明由等截面段、扩张段和等截面段构成的超音速燃烧室,通过一定的喷油方式,能按飞行状态可分别实现超音速燃烧和亚音速燃烧,从而达到把超燃冲压发动机的工作范围下限扩大到飞行马赫数为3。
短句来源
  相似匹配句对
     b) combustion control;
     b燃烧控制;
短句来源
     combustion & heat transfer;
     燃烧和传热;
短句来源
     The Predication of Subsonic Diffusers(2)
     亚音速扩压器计算(二)
短句来源
     PREDICTION OF PERFORMANCE OF SUBSONIC DIFFUSER
     亚音速扩压器性能计算
短句来源
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  subsonic combustion
The difference between supersonic combustion and subsonic combustion is discussed, and the mechanism of supersonic combustion propagation and the limitation of heat addition in supersonic flow are pointed out.
      
Fast subsonic combustion of gases in an inert porous medium with a smooth rise in the pressure in the wave
      
Although the flows have their most natural application in the design of ramjets, some of them could also be applicable to afterburners or other subsonic combustion chambers.
      
A ramjet with subsonic combustion of kerosene fuel will be used to reduce the engine development risk.
      


In this paper the principle and current condition of study are described that how totransfer subsonic combustion into supersonic combustion in chamber. The experiment shows thevariations of parameters at sections along combustor and the effects of injector location and fuel/airratio on combustion state

描述了在超音速燃烧室中如何从亚音速燃烧模态转变为超音速燃烧模态的概念和目前的研究状态,并用实验表明改变氢燃料喷射位置和当量比对燃烧状态的影响,以及燃烧室各截面参数的变化规律。

In this paper,a supersonic combustor formed of a segment with constant cross section,a divergent segment and a segment with constant cross section is designed,and do combustion tests with it It is indicated by one dimensional calculation that supersonic combustion or subsonic combustion can be realized as flight speeds with the supersonic combustor formed of a segment with constant cross section,and by different fuel supplied ways,which makes the flight lower limit of Scramjet engine extended up to flight...

In this paper,a supersonic combustor formed of a segment with constant cross section,a divergent segment and a segment with constant cross section is designed,and do combustion tests with it It is indicated by one dimensional calculation that supersonic combustion or subsonic combustion can be realized as flight speeds with the supersonic combustor formed of a segment with constant cross section,and by different fuel supplied ways,which makes the flight lower limit of Scramjet engine extended up to flight Mach number 3

本文设计了由等截面段、扩张段和等截面段构成的超音速燃烧室,并进行了燃烧实验。用一维计算分析实验结果,表明由等截面段、扩张段和等截面段构成的超音速燃烧室,通过一定的喷油方式,能按飞行状态可分别实现超音速燃烧和亚音速燃烧,从而达到把超燃冲压发动机的工作范围下限扩大到飞行马赫数为3。

 
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