Mobile
Log In Sign Up
Home > english-chinese > "喷管结构" in Chinese

Chinese translation for "喷管结构"

nozzle structure

Related Translations:
涡轮喷管:  turbine nozzle
低速喷管:  slow running jet tubeslow-running jet tube
铰接式喷管:  hinged nozzle
喷管端点:  end of the nozzle point
喷管倾斜:  cant of the jet
可变喷管:  variable nozzle
膨胀喷管:  expansion nozzle
喷管根部:  nozzle-end
反向喷管:  reversal nozzle
喷管架:  nozzle tube yoke
Example Sentences:
1.The machining , installation , debug of the nozzle are completed after its design , and the finial running results of the nozzle are provided
喷管结构设计完成后进行喷管加工、安装、调试,最终给出喷管实际调试结果。
2.Equality design method was used in numerical simulations , and multiobjective optimization method was used to design the scramjet nozzle configuration
通过均匀设计法设计仿真算例,并通过多目标优化设计方法设计出了性能较好的喷管结构
3.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。
4.( iii ) the structure design of the nozzle is completed according to coordinate data of the nozzle contour . the airproof design problem and the throat - cooling problem are mainly solved during the structure design
(三)根据喷管型面坐标数据进行喷管结构设计,在喷管结构设计中着重解决密封设计和喉道冷却等问题。
5.Variation tendency of nozzle gap and contact stress was obtained in terms of multi - time computational results , and some modification suggestions , which are available for designers of solid rocket motor nozzle , were presented by the tendency
综合多个时刻的计算结果得到发动机工作过程中喷管结构缝隙和接触应力的变化趋势,并据此对设计缝隙提出了修改意见,结果可为发动机喷管设计提供参考。
6.The effects of such elements as primary flow total pressure , flow rate , degree of fuel rich , nozzle structure , flying speed and secondary combustion on ejecting mode performance were researched . it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0 . 7 . to deeply analyze thrust augmentation mechanism in low speed range , the research was further continued by changing secondary combustion organization and aft - body configuration
研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响,发现实验样机构型在0 . 7ma以上的飞行条件下可以获得推力增强,而在0 . 7ma以下无推力增强。
Similar Words:
"喷管间距" Chinese translation, "喷管减压出口" Chinese translation, "喷管角修正因数" Chinese translation, "喷管截面积" Chinese translation, "喷管截面积比" Chinese translation, "喷管进口" Chinese translation, "喷管进口的给定条件" Chinese translation, "喷管进口的气体参数" Chinese translation, "喷管进口气流马赫数" Chinese translation, "喷管进口条件" Chinese translation