combustor

Therefore by regulating swirl number of combustor NO emission caw be reduced.

因此,适当调整燃烧室的旋流数可以降低NO排放.

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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.

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These results can provide some reference for maintain and design for gas turbine combustor.

本文研究结果可为发动机火焰筒的维修和改进设计提供参考.

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Computations are done on flow configurations that resemble the reaction zone in the scramjet combustor flows.

本文通过数值模拟得到了超燃冲压发动机燃烧室化学反应流流场的流动结构.

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Numerical simulation of temperature field in controllable active thermo-atmosphere combustor

可控活化热氛围燃烧器温度场的模拟

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Multi-zone coupling method is adopted to simulate three-dimensional two-phase reacting flow field in the annual combustor with a triple swirler in arbitrary curvilinear coordinates.

在三维曲线坐标系下采用多区域耦合法对包括三级涡流器在内的环形燃烧室三维两相反应整体流场进行了数值模拟。

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The annular multi-hole radial jets have important effect on combustor liner.

环向径向射流对燃烧室火焰筒内的流场有着重要的影响.

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The experimental results of the axial velocity and the tangential velocity in combustor have been given.

给出了燃烧室内的轴向速度和切向速度的试验结果.

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All these works done were hoped to be available for the combustor configuration design.

为燃烧室结构设计与设计参数选择提供了参考.

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Increasing the combustion efficiency of the micro combustor to the greatest extent is very important to the micro thermophotovoltaic systems.

最大化提高微燃烧室的燃烧效率对于微热光电系统是非常关键的。

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The Study of Gas Turbine Combustor Using Chemical Reactor Network Approach

燃气轮机燃烧室化学反应器网络模型研究

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The fragmentation char combustion behavior in a fluidized bed combustor.

利用下行气流振动床代替流化床,研究了煤的碎裂特性.

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Fig. 2 Schematic of the combustor model.

图2微燃烧器数值模型内部结构.

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The experimental results show that autoignition was sensitive to a number of parameters: air stagnation temperature and pressure, and wall configuration of the combustor, The temperature and wall configuration has significant effect on the autoignition.

发现滞止温度、滞止压力和燃烧室内部构型等都对自燃有影响，特别是滞止温度和内壁构型的影响非常大。

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Study on Micro Combustor for Micro Thermophotovoltaic System

微热光电系统燃烧器的研究

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Either stall or surge may result in combustor blowout.

不管是喘振或者爆音,都将引起燃烧室的熄火.

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A mathematical model describing combustion in a high pressure liquid hypergolic bipropellant ( UDMH/ H2O4) rocket engine combustor has been developed.

本文提出了一个高压液体双组元自燃推进剂火箭发动机燃烧室计算模型。

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Totally 4 combustor groups are there at the front and back of boiler.

锅炉前后各有两组燃烧器,每三个燃烧器为一组,共有4组.

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Numerical study of reacting flow field in the annual combustor with the tripe swirler

三级涡流器环形燃烧室化学反应流场的数值研究

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Developing Metal Fiber Combustor To Improve Natural Gas Application Technology

开发金属纤维燃烧器&提高天然气应用技术

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Investigation Progress on Release and Control of NO_x and N_2O during Coal Combustion in Circulating Fluidized Bed Combustor

循环流化床燃煤过程NO x和N2O产生-控制研究进展

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Flame-out protection device: Wher the combustor quenches by accident , combustion proportional value will be closed automatically.

熄火保护功能: 燃烧器以外熄火时, 燃气比例阀自动关闭.

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Study on high-sulfur coal combination fuels for fluidized be combustor by the method of thermogravimetry analysis

用热重分析（TGA）方法研究高硫煤流化床混合燃料

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By optimizing ejector combustor geometry, ejector rocket in SMC combustion mode can obtain comparable thrust augmentation.

通过优化引射器后体结构, 在SMC二级燃烧模式下工作的引射火箭可以产生较大的推力增强.

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Measurements were also time-averaged gas temperature and species concentrations in the combustor.

同时还测量了该燃烧室内气体平均温度和组分浓度分布.

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Micro combustor is one of the most important components in a micro-thermo-photovoltaic MTP system.

最大化提高微燃烧室的燃烧效率对于微热光电系统是非常关键的.

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Using the FLUENT software and chemical reactor network, the pollutant emission from the combustion chamber is calculated. Referring to the prototype combustor, we get the ultimate pollutants emission.

使用FLUENT软件和化学反应器网络法对该燃烧室的污染物生成及排放进行计算，参照原型燃烧室的出口NOx排放量，确定其最终的出口污染物排放值。

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In this thesis, numerical simulations of three-dimensional turbulent reacting flow in gas turbine combustor were studied.

本文针对含有强旋流的燃气轮机燃烧室三维湍流反应流的数值模拟问题进行了研究。

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Boron particle combustion model and turbulent no-premixed combustion model were established by using King theory and probability density function in order to study the reacting fuel-rich flow field laden with boron particle in the ramjet combustor. Some obtained numerical results were tested by examination.

以King模型模化硼粒子燃烧，以几率密度模型模化湍流燃烧，对含硼贫氧推进剂固体火箭冲压发动机补燃室流场进行数值研究，并与试验结果进行了对比。

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In order to simulate parameters of different diesel exhaust heat, an simulative multi-heat testing flat is set up with an combustor and two fans.

采用燃烧器和两个离心风机构成的二级送风系统组成模拟多热源实验台，以模拟不同的内燃机余热条件。

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