1+1对转涡轮气动设计技术研究

Aerodynamics design of two-stage counter rotating turbine

  • 摘要: 分析了对转涡轮方案的影响因素,推导了带导叶对转涡轮基元级速度三角形参数与涡轮效率和出功比的关系,进行了速度三角形的分析,得到了带导叶对转涡轮速度三角形的设计规律。为验证此规律,选取了基元级基本参数,在此基础上,进行了考虑冷却的1+1对转涡轮气动方案的设计;并利用三维数值模拟手段对所设计的气动方案进行了验证。结果表明,所完成的涡轮气动方案能够满足设计要求,且选取的速度三角形基本参数与数值模拟结果较为接近。

     

    Abstract: In order to investigate the influence of jets width on detonation initiation via imploding annular shock waves, detonation initiation with different jets width were simulated and hydrogenair mixture was used. The results indicate that when jets temperature is constant, different jets width exist different critical jets pressure, when jets pressure Pin is higher than the critical jets pressure, imploding annular shock waves can form high pressure and high temperature region that lead to direct initiation; the critical jets pressure increased with the increase of jet width.

     

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