尾喷管的英文

发音:

"尾喷管"怎么读用"尾喷管"造句

英文翻译手机版

exhaust cone
exhaust tail pipepiston
exit cone
jet tail cone
jet-pipe nozzle
propelling nozzle
tail nozzle
tailpipe nozzle

"尾"英文翻译 hairs on a horse's tail spik ...
"机身尾喷管" 英文翻译 : fuselage tailpipe
"平直尾喷管" 英文翻译 : plain tailpipe
"倾斜尾喷管" 英文翻译 : tilting tailpipe
"尾喷管套" 英文翻译 : tailpipe lagging
"尾喷管温度" 英文翻译 : jpt
"鱼尾喷管" 英文翻译 : fishtailed downcomer
"眼脸式尾喷管" 英文翻译 : clam shel nozzle
"可调节尾喷管锥体" 英文翻译 : movable bullet; throat bullet
"喷气机尾喷管色" 英文翻译 : jet exhaust
"尾喷管出口温度" 英文翻译 : jet tailpipe
"尾喷管调整窗口" 英文翻译 : rocket nozzle adjustment access
"尾喷管内的燃烧" 英文翻译 : tailpipe burning
"泵吸管尾管船尾喷管" 英文翻译 : tail pipe
"可调节的尾喷管锥体" 英文翻译 : movable bullet; throat bullet
"尾喷管锥体固定杆端头固定装置" 英文翻译 : bullet-strut end fixing
"尾喷口" 英文翻译 : final nozzle; jet nozzle; tailing spout
"喷管" 英文翻译 : atomizer device; atomizer pipe; augmenter tube; blast tube; duct; effuser; exhaust cone assembly; injection pipe; inlet bend; inlet elbow; jet pipe; jet tube; lance; metal nozzle; mouthpiece; nozzle pipe; nozzle tube; rod pipe; spray bar; spray pipe; sprayer nozzle; thrust jet
"鼠尾喷灯" 英文翻译 : rat-tail burner
"鱼尾喷灯" 英文翻译 : fish-tail burner
"鱼尾喷嘴" 英文翻译 : fishtail spray
"喷气机的尾喷" 英文翻译 : jet blast
"无尾喷气式飞机" 英文翻译 : tailless jet
"磁喷管" 英文翻译 : magnetic nozzle
"方喷管" 英文翻译 : blow line

例句与用法

This engine consists of an inlet, a combustor, and a nozzle .
这台发动机由一个进气道，一个燃烧室和一个尾喷管组成。
Scramjet nozzle was installed at the exit of the combustor
尾喷管直接安装在模型发动机的燃烧室出口。
Check the engine tail pipe on metal particles and visible damage
检查发动机尾喷管无金属颗粒和损坏。
In final section of this paper , the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed
最后，本文针对两种构型的超音速尾喷管，对其流场进行了计算和分析。
The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle
由于高超声速飞行器机体与发动机高度一体化的构型,使超燃冲压发动机尾喷管具有非对称,面罩可调等特点。
In this paper , experimental and computational methods were introduced to study the characters of scramjet nozzle and to guide the design
为了解超燃冲压发动机的工作特性,并设计其合理的构型,本文采用试验和仿真两种方法对超燃冲压发动机尾喷管进行了研究。
The engines would have variable nozzles , which would be fully opened on take - off and landing , so that the exhaust would be slow and relatively quiet , and narrowed when the aircraft was cruising , providing the necessary speed
引擎将配有大小可以调节的尾喷管：起飞和降落时会全部打开，这样喷气速度会下降、噪音也会更小；而巡航飞行过程中，尾喷管将变小以保证必要的飞行速度。
To meet the needs for wider surge margin of the turbofan engine , a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis . several ways , including , variable inlet guide vanes of the fan , variable guide vanes of the high pressure compressor , the variable inlet area ratio of the mixer and the nozzle areas , were presented to enlarge the surge margin of the turbofan engine . meanwhile , a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan , guide vanes and the first two stators of high pressure compressor , area ratio of mixer and noz zle areas was established
为了满足下一代作战飞机对推进系统的性能和稳定性要求，本文建立了压缩系统特性和涡轮特性的新模型，并分别采用改变涡扇发动机风扇进口导流叶片、压气机导流叶片和前两级静叶片、混合室进口处内、外涵面积比和尾喷管面积，研究了其对发动机性能和稳定性的影响，进而得出了涡扇发动机变几何扩稳的方法，为发动机变几何扩稳研究打下理论基础。
In arbitrary curvilinear coordinate systems , three dimensional turbulent combustion flow fields of the three kinds of turbofan engine afterburner with the longitudinal heat shield 、 outer cold flow and the jet nozzle are simulated . the three - dimensional body - fitted grids are generated by an elliptical grid generation procedure and zone method
本文在任意曲线坐标系统下对三种带有纵向隔热屏、外冷却通道和尾喷管的涡扇发动机加力燃烧室的三维紊流燃烧流场进行数值模拟。