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燃烧室出口
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  “燃烧室出口”译为未确定词的双语例句
     The combustion efficiencies were 0.82, 0.67 and 0.60, respectively.
     燃烧室出口的燃烧效率分别为0·82,0·67和0·60。
短句来源
     Aerodynamic functions with method of flow-obstrinction was employed to compute flow parameters,combining aerodynamic calculation and jet flow mixing temperature disposal.
     利用气动函数结合流阻法进行流动参数计算,采用气动方法计算射流穿透深度和掺混温度,得出相应掺混孔改变量与掺混气变化量及相应燃烧室出口截面处的温度变化量.
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     The combustion chamber's exergy efficiency,in case biomass fuel gas is used,compared with respective cases of using two kinds of coal gas with different heating values,all under the same condition of 1147°C temperature at the combustion chamber's exit,shows that the exergy efficiency is relatively lower for both kinds of coal gas with different heating values and that of biomass fuel gas highest.
     对生物质燃料气、两种不同热值煤气在燃烧室出口燃气温度为1147℃时的燃烧室的效率进行了比较,两种不同热值煤气的效率较低,生物质燃料气效率最大。
短句来源
     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
短句来源
     The elementary experiment results show that the device can keep steady combustion and the temperature of the flame center is about 1150-1260℃ at the outlet of the main combustion chamber, and that the ratio of the input power of arc plasma to the thermal power of coal powder is about 1 : 25.
     经初步实验研究,这种燃烧器能稳定地燃烧,主燃烧室出口处火焰中心温度约为1150-1260℃,输入的等离子体功率与所进煤粉燃烧的热功率之比约为1:25。
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  相似匹配句对
     DETERMINATION OF FACTOR K FOR ASCERTAINING PEAK TEMPERATURE AT COMBUSTOR EXIT
     燃烧室出口热点温度系数的确定
短句来源
     The stabilization investigation of the combustor exit temperature field in aeroengine
     航空发动机燃烧室出口温度场稳定性的研究
短句来源
     Export Procedures
     出口手续
短句来源
     Export Substitation
     出口替代
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     3. Combustion chamber design.
     燃烧室设计;
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The exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally on a two-dimensional experimental combustor. According to the results the effect of different configurations of dilution hole design on combustor exit radial temperature profile shows certain regularity. A semi-empirical and semi-analytical model has been developed for predicting the exit temperature profile of gas turbine combustor.The model can predict the effect of change in dilution...

The exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally on a two-dimensional experimental combustor. According to the results the effect of different configurations of dilution hole design on combustor exit radial temperature profile shows certain regularity. A semi-empirical and semi-analytical model has been developed for predicting the exit temperature profile of gas turbine combustor.The model can predict the effect of change in dilution zone design or combustion operating conditions on the variation of combustor exit radial temperature profile based on exit temperatures meas-sured before change. The comparison of the predictions with the measurements shows excellent agreement. The model provides a quantitative design tool for adjustment of temperature profile of gas turbine combustor.

在二元试验燃烧室上,研究了四种掺混孔设计方案对燃烧室出口径向温度分布影响。结果表明,不同掺混孔设计方案对出口径向温度分布的影响有规律可循。本文建立了半经验半分析模型,能够由第一次试验得到的出口温度分布,推算修改后出口径向温度分布曲线的变化。模型计算结果和试验结果吻合。

On a two dimensional experimental combustor exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally.The inlet air is of room temperatire,and the combustor temperature rise ranges from 280℃to 570℃,and the combustor pressure is atmospheric pressure.From the experimental results the effect of different configurations of dilution hole desion on combustor exit radial temperature profiles showe 1 certain regularity.In the present study,a semi-empirical...

On a two dimensional experimental combustor exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally.The inlet air is of room temperatire,and the combustor temperature rise ranges from 280℃to 570℃,and the combustor pressure is atmospheric pressure.From the experimental results the effect of different configurations of dilution hole desion on combustor exit radial temperature profiles showe 1 certain regularity.In the present study,a semi-empirical & semi-analytical model has been developed for predicting the exit radial temperature profiles from gas turbine combustors.The model can predict the effect of change in dilution zone design or combustor operating conditions on the change of combustor exit radial temperature profiles based on exit temperature measurement before the change.The predictions have been compared with the measured exit radial temperature profiles,the comparison showed excellent agreement.The model provides a quantitative design tool for the adjustment of temperature profile of gas turbine combustor.

本文在二元试验燃烧室上,对四种掺混孔设计方案作了燃烧室出口径向平均温度分布的试验研究。试验时燃烧室进口不加温,温升范围280°~570℃,燃烧室出口为常压。试验结果表明:不同掺混孔设计方案,对燃烧室出口平均径向温度分布的影响是有规律可循的。本文同时建立了预估燃气涡输发动机主燃烧室出口平均径向温度分布的半经验半分析模型。该模型能够由第一次试验得到的出口温度分布,推算出燃烧室掺混区设计修改后或工作状态改变后,燃烧室出口平均径向温度分布曲线的变化。模型计算结果和从二元试验燃烧室出口测得的平均径向温度分布非常吻合,为调试燃烧室出口平均径向温度分布提供了定量的设计工具。

The experiment research results are obtained which a bench-scale atmospheric combustor utilize CWS as fuel. For the combustor and combustion of CWS, a method of calculate combustion efficiency is given by measure CO2% of combustor exit.

本文给出了一个卧式常压燃烧装置,以CWS为燃料的试验研究结果。并根据本装置结合CWS的燃烧,给出了通过测量燃烧室出口烟气中CO_2%,以计算出燃烧效率的方法。

 
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