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   secondary nozzle 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.084秒
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secondary nozzle
相关语句
  二次喷管
    Unstructured mesh was used in 3-D numerical simulation to simulate the influence of secondary nozzle on performance of rocket ejector, ejecting ability and mixing condition.
    应用非结构网格技术对引射火箭的流动进行了三维湍流数值模拟,分析了二次喷管对引射火箭总体性能、引射能力和混合状况的影响。
短句来源
    It is shown that when the exit area of secondary nozzle and the fuel/oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. The synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design.
    结果表明:在固定二次喷管出口面积和氧/燃比的条件下,二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加,二者综合作用使发动机推力增加,但增幅不大,表明在设计发动机结构和工作参数时,不必过分追求大的引射系数;
短句来源
    The results indicate that with decrease of exit area of secondary nozzle, the bypass ratio is decreasing, and the static pressure in integrated ejector combustor is increasing, and mixing condition becomes better.
    结果表明:引射能力随着二次喷管出口面积的减小而减小; 整体式引射燃烧室压强随着二次喷管出口面积的减小而上升,混合随之更为充分;
短句来源
    There exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector.
    存在一个最优的二次喷管出口面积,使发动机推力最大。
短句来源
    The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
    研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响,找到了逐步提高推力的措施。
短句来源
更多       
  二次喷管
    Unstructured mesh was used in 3-D numerical simulation to simulate the influence of secondary nozzle on performance of rocket ejector, ejecting ability and mixing condition.
    应用非结构网格技术对引射火箭的流动进行了三维湍流数值模拟,分析了二次喷管对引射火箭总体性能、引射能力和混合状况的影响。
短句来源
    It is shown that when the exit area of secondary nozzle and the fuel/oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. The synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design.
    结果表明:在固定二次喷管出口面积和氧/燃比的条件下,二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加,二者综合作用使发动机推力增加,但增幅不大,表明在设计发动机结构和工作参数时,不必过分追求大的引射系数;
短句来源
    The results indicate that with decrease of exit area of secondary nozzle, the bypass ratio is decreasing, and the static pressure in integrated ejector combustor is increasing, and mixing condition becomes better.
    结果表明:引射能力随着二次喷管出口面积的减小而减小; 整体式引射燃烧室压强随着二次喷管出口面积的减小而上升,混合随之更为充分;
短句来源
    There exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector.
    存在一个最优的二次喷管出口面积,使发动机推力最大。
短句来源
    The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
    研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响,找到了逐步提高推力的措施。
短句来源
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  secondary nozzle
When the gas is expanded in the secondary nozzle to static temperature values corresponding to the conditions of free flight, an exact simulation of the latter is possible at an altitude H= 65 to 70 km (u= 7.5 km/s, M = 20 to 25).
      
The air-liquid mixture shall then be discharged into the secondary nozzle and, hence horizontally into the basin.
      
In addition, primary and secondary jet velocity and turbulence components were measured at the centre of primary and secondary nozzle exits.
      


The utilization of rocket ejector is important to structural integration of RBCC, for it may decrease weight and complexity of the motor. Numerical simulation and experimental approaches are adopted in the paper to investigate the influence of secondary nozzle on the performance of rocket ejector. In the theoretical aspect, unstructured meshes are used in 3-D numerical simulation. The results indicate that along with decreasing exit area of secondary nozzle, the bypass ratio decreases, the static...

The utilization of rocket ejector is important to structural integration of RBCC, for it may decrease weight and complexity of the motor. Numerical simulation and experimental approaches are adopted in the paper to investigate the influence of secondary nozzle on the performance of rocket ejector. In the theoretical aspect, unstructured meshes are used in 3-D numerical simulation. The results indicate that along with decreasing exit area of secondary nozzle, the bypass ratio decreases, the static pressure in integrated ejector combustor increases. There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.

利用引射火箭试验系统和固体火箭发动机燃气发生器,就不同结构的二次喷管对引射火箭的性能影响开展了试验和数值模拟研究。模拟计算和试验结果表明,二次喷管降低了发动机的引射系数,但改变了燃烧室的压强分布,使其推力特性得以改善。在文中所研究的引射燃烧室结构条件下,存在一个最佳二次喷管出口面积,它能使引射火箭的推力达到最大。

 
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