Chinese translation for "bypass ratio"

涵道比
函道比
旁路比
旁通比

Related Translations:

bypass:  n. 【机械工程】(煤气等的)旁(通)管；(为疏散交通而设的迂回的)旁路；小道，间道；【电学】分路迂徊。2.vt. 为…加设旁路[旁通管]；绕过，越过，超过；回避，忽视(by-pass a congested city 加设旁路疏散拥挤的城市交通。 bright sunshine by-passing the thin curtains 强烈的阳光透过薄窗帘。 by-pas

bypassing:  分路作用回避旁路；错误传达旁通

bypass condenser:  旁路电容器

bypass gastrojejunostomy:  分流性胃十二指肠吻合术

bypass path:  旁路通路

arterial bypass:  动脉旁路术

bypass road:  绕道公路绕行道路外环道

bypass arm:  旁通臂旁通阀桥臂

complement bypass:  补体旁路

bypass manifold:  旁通歧管

Example Sentences:

	1.	Modern low bypass ratio turbofan engine is the heart of the new fighter , whose performance and aerodynamic stability greatly affect the characteristics of the new fighter 涡扇发动机作为现代战斗机的心脏，其性能和稳定性对战斗机的性能和稳定性能有很大的影响。
	2.	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 . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector 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；存在一个最优的二次喷管出口面积，使发动机推力最大。
	3.	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 . in the comparison between two configurations , the typical one has better performance , indicating the importance of pressure ratio 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；两种结构的性能对比分析表明了增压比对引射火箭性能的提高具有重要意义；对引射火箭的热力循环分析同样表明，增压比对于提高发动机性能非常关键。
	4.	By adjusting many variable geometry components of the engine , bypass ratio can be changed during large range ( the most 0 . 25 of military fighter ) . the high specific thrust characteristic of turbojet engine and the low specific fuel consumption characteristic of the turbofan engine can be realized during different flight phase by the usage of vce technology 变几何变循环发动机是应用于第四代多用途战斗机的理想动力装置，通过多个部件几何的调节在较大范围内改变涵道比，能够使发动机在不同航段分别实现涡喷发动机的高单位推力性能和涡扇发动机的低油耗性能。
	5.	These variable geometry components include high pressure - compressor , high - pressure turbine , low - pressure turbine , inlet area ratio of mixer and main nozzle throat area . the results of calculation show that the adjusting of low - pressure turbine and mixer has a remarkable effect on the performance of engine and bypass ratio 计算结果表明，低压涡轮和混合器的调节对发动机的性能和涵道比的影响尤为显著；在其它部件几何结构不同时，单个部件几何调节后，发动机性能的变化趋势是不同的。
	6.	The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate , but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow . the expansion configuration shows low thrust property due to low pressure in flow path . the secondary nozzle changes the pressure distribution in ejector combustor , and decreases bypass ratio , but obtain more completely mixing 结果表明：二次流流量随着一次流流量的增加而增加，由于二次流流量的增加速度低于一次流，引射系数减小；在纯扩张式结构实验中，引射燃烧室压强很低，难以实验推力增强；二次喷管改变了引射燃烧室的压强分布，降低了引射系数，改善了混合状况能；对于本文的实验结构，存在一个最优的二次喷管出口面积，使引射火箭推力最大，同数值模拟结果相吻合。

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