( 3 ) under the ideal conditions of no particle deposition , the complex effects of flow parameters and geometry on performance of microfiltration with outside helical flow were discussed . and it is suggested that when designing , several factors should be taken into account comprehensively . it is noted that increasing mf capability will , at the same time , increase the energy loss of the module ( 3 )综合分析了在无颗粒沉积的理想情况下，流动参数、结构参数对微滤效果的影响情况，发现各参数对微滤效果的影响复杂，在膜器优化设计时必须综合考虑各因素而适当选取，且微滤效果的提高是以过膜器压力损失的增大为代价的，从而从理论上对实际微滤过程中观察到的通量随操作压力的增大而增大的现象做出了解释。
Process tomography ( pt ) techniques , which has been development rapidly in recent several ten years , have made certain progress in field of measurement of two - phase flow / multiphase flow parameter ' s distribution status . it might become a means for two - phase flow measurement and could be widely applied in industry 近十几年发展起来的过程层析成象( pt )技术在两相流多相流流动参数分布状况的测量方面取得了一定的进展，有可能成为解决两相流参数检测的有效手段，具有很大的潜力和广阔的工业应用前景。
The coupling from the pulse jet in the nozzle to the unsteady flow in the tube was discussed . and the relations between the parameters of gas charge and discharge , structure , working , flowing in tube and ideal cooling efficiency were established . the theory foundation of the influence of pulse jet on the flowing in the tube and characteristic would be built 探讨了脉动射流与管内非定常流动的耦合问题,建立了脉动射流有关参数如进、排气参数、结构参数、运行参数等和振荡管内流动参数及理想制冷效率之间的普遍联系,为研究脉动射流参数对振荡管内流动及其性能的影响打下了理论基础。
To satisfy the practical need of internal cooling in turbine blades of aeroengine , some detailed experimental measurements on the discharge coefficients , pressure coefficients and flow field in the internal passages with both rib - roughened walls and film hole suctions under a wide range of aerodynamic parameters . and the interrelated numerical simulation was also been implemented 本文根据航空发动机中涡轮叶片内流冷却的实际需要，在宽广的气流流动参数范围内，对同时带肋和气膜孔出流的叶片内冷通道的流量系数、压力系数以及流场进行了详细的实验测试，同时还进行了相应的数值模拟计算。
To satisfy the practical need of film cooling in turbine blades of aeroengine , some detailed experimental measurements on the flow field in the channel with the holes on the wall and in the holes had been completed within a wide range of aerodynamic parameters . and the interrelated numerical simulated compute had also been implemented 本文根据航空发动机中涡轮导向叶片气膜冷却的实际需要，在宽广的气流流动参数范围内，对叶片内冷通道的流场进行了详细的实验测试，同时还进行了相应的数值模拟计算。
