combustor

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.

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.

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.

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.

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.

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.

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.

Fig. 2 Schematic of the combustor model.

图2微燃烧器数值模型内部结构.

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.

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.

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.

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.

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.

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.

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.