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燃烧
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  combustion
    Combustion Flow Investigation in Ejecting Mode of RBCC
    火箭基组合动力循环(RBCC)引射模态燃烧流动研究
短句来源
    Basic Study on a Nonflame Combustion Technique with Thermal Cyclic Carrier of Molten Salt
    熔融盐循环热载体无烟燃烧技术的基础研究
短句来源
    Studies on Laser Spectroscopy Technology and Its Application to Combustion Diagnosis in the Jet Engine
    激光光谱诊断技术及其在发动机燃烧研究中的应用
短句来源
    Study on Primary Combustion of Boron-based Fuel-rich Propellant
    含硼富燃推进剂一次燃烧研究
短句来源
    Theoretical, Numerical Simulation and Experimental Investigations of Combustion Instability in Liquid Rocket Engine
    液体火箭发动机燃烧稳定性理论、数值模拟和实验研究
短句来源
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  combust
    Reciprocating superadiabatic combustion in porous media(RSCP) is a advanced technique with great potential by which flammability limits of fuels can be significantly extended and premixed gases with extremely low heat content can combust steadily while the emission of NOX and CO can be reduced greatly.
    多孔介质内的往复流动超绝热燃烧技术可以拓宽燃料可燃极限,实现超低热值预混合气的稳定燃烧,并可显著降低尾气中NO_x和CO的排放,因而是一项很有发展潜力的先进燃烧技术。
短句来源
    A computer program was developed based on the minimum free energy algorithm, The program consists of several compute modules including assumption chemical molealar formula calculation, final combust resultant calculation of combusting chamber nd combustion temperature calculation in steady pressure etc.
    编写了用最小自由能法计算的通用热力计算程序,程序中主要包括了假定化学式求解、计算燃烧室中平衡组分和确定燃烧产物定压燃烧温度等几个计算模块。
短句来源
    Due to extremely short residence time of supersonic airflow, it is difficult to effectively mix and combust for the fuel and air in scramjet combustor.
    高超声速气流在燃烧室的停留时间非常短,使得超燃冲压发动机燃烧室内燃料与气流的混合及其燃烧变得非常困难。
短句来源
  “燃烧”译为未确定词的双语例句
    Design Techniques for integrated Rocket-Ram/Scramjets
    整体式火箭-冲压发动机/超音速燃烧冲压发动机的设计技术
短句来源
    Optimum Design of Scramjet Engine
    超音速燃烧冲压发动机最佳设计参数
短句来源
    A RESEARCH ON EXPLOSIVE PROBLEM IN END-BURNING SOLID PROPELLANT ROCKET MOTORS
    端面燃烧固体火箭发动机的爆炸问题研究
短句来源
    AN INVESTIGATION OF THE DEFLAGRATION-TO-DETONATION TRANSITION OF THE AP/HMX/HTPB COMPOSITE PROPELLANT
    AP/HMX丁羟复合推进剂燃烧转爆轰研究
短句来源
    An Experimental Study of Deflagration - to - Detonation Transition on a Model NEPE Propellant
    模型NEPE推进剂燃烧转爆轰实验研究
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  combustion
According to combustion phenomenon, polymer 4 was supposed to be processed with a good flame-retardant property because of its excellent crosslinked structure during pyrolysis or combustion.
      
Preparation of nanometer MgO by sol-gel auto-combustion
      
Nanometer MgO was prepared via a sol-gel auto-combustion technique using magnesium nitrate as raw material and citric acid as chelating agent.
      
By studying the different TG curves of magnesium citrate gel prepared by different methods, we found that a combustion process occurred and the nitrate ions acted as an oxidant in the combustion process.
      
TEM photographs of synthesized powders from the sol-gel auto-combustion showed that the crystallites were uniform in size.
      
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  combust
The method permits the determination of nitrogen even in compounds difficult to combust under normal conditions.
      
The device is actually the multiple microflame quartz-tube atomizer (multiatomizer) with inlet arm modified to serve as the trap and to accommodate the oxygen-delivery capillary used to combust hydrogen during the trapping step.
      
In particular, organic samples containing nitrogen (N) or halogen atoms combust to products which are especially well detected with high sensitivity.
      
Fluids Eng.122 (2000) 830-835; Gibson, C.H., Combust.
      
Model equation for the probability distributions of the velocity and concentration during turbulent mixing and diffusion combust
      
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A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of this method,the...

A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of this method,the combustion efficiency of “C” engine is calculated.Comparison of calculated Combustion efficiencies with experimental results shows satisfactory agreement with errors within 1-5%.Curves of total vaporization rate of fuel and vaporization rate per unit length as functions of the axial distance of combustor for given rocket engine are also presented.These curves show that the effects of decomposition reaction,secondary atomization of droplets and drop size distribution on vaporization rate are very substantial.Finally, the conditions,under which this model can be used,are discussed

本文提出了一个自燃推进剂液体火箭发动机燃烧室设计简化模型。与 Priem 基本模型不同,本文考虑了燃料分解反应,液滴二次雾化以及燃烧室截面上混合比和流强的不均匀性对燃烧效率的影响。文中导出了计算所需的全部公式,提出了计算程序。应用本方法计算了 C 发动机的燃烧效率。计算效率与试验结果相当符合,其误差在1~5%以内。文中还给出了燃料总蒸发速率和单位长度上的蒸发速率随该发动机燃烧室轴向距离变化的曲线。曲线表明,分解反应,液滴二次雾化和液滴尺寸分布对蒸发速率的影响很大。最后讨论了本模型使用的条件。

A Computer program of the hot starting and shutdown transients of a simple pressurized liquid bipropellant rocket engine is given,based upon the idea and basic equations provided by W.T.Webber etal.and mainly applying priem's combnstion model and feeding system distribution para- meter model.The hot starting and shutdown transients are calculated on 441B-Ⅲ digital computer and the elementary results arc obtained.

本文依据 W.T.Webber 等人提供的思路和基本方程,基本采用了 Priem 的燃烧模型和管路系统分布参数模型,为简单的挤压式双元液体推进剂火箭发动机热启动——关车瞬变工作过程编写了计算机程序,并在441B—Ⅲ型电子计算机上进行了计算,得出了初步的结果。

In studying the combustion of Double Base (D.B) propellants a coulometric nitrogen oxides detector, differential scanning calorimetry ( DSC ) and a long-focus microphotographic camera were used to determine respectively the amounts of NO2, NO the dissociation heat Q and the activation energy E and the dark zone thickness L. The results are as follows. decreaseswherePropellant A catalyzed high burning rate propellantPropellant O noncatalyzed propellant for contrastPropellant B catalyzed plateau propellantwhere...

In studying the combustion of Double Base (D.B) propellants a coulometric nitrogen oxides detector, differential scanning calorimetry ( DSC ) and a long-focus microphotographic camera were used to determine respectively the amounts of NO2, NO the dissociation heat Q and the activation energy E and the dark zone thickness L. The results are as follows. decreaseswherePropellant A catalyzed high burning rate propellantPropellant O noncatalyzed propellant for contrastPropellant B catalyzed plateau propellantwhere F represents the peak area per 1mg propellantIt can be seen from the analysis of the above results that in the combustion process of the double base propellant there must be a gas-solid heterogeneous reaction between NO2 and the propellant, and this reaction is an important step that affects the combustion rate of the propellant. Rate increasing catalysts will catalyze this reaction, as a result, the burning rate can be increased greatly.Inhibition of such a reaction by plateau catalysts is one of the factors that produce the plateau.Both sets of catalysts are effective in the dark zone, but they have no remarkable effect on the burning rate.

本文选用库仑法测定NO_2、NO,DSC测定分解热(?),活化能(?),长焦距显微摄影测暗区厚度L。对三种推进剂:空白推进剂O,增速推进剂A,平台推进剂B进行了研究。结果如下(以F表示1mg推进剂放出NO_2峰面积) NO_2/NO F_2mg/F_(0.4)mg (?)mcal/mg (?)大卡/克分子 L 推进剂A 7.1% 0.63 478 35 略减薄 推进剂O 11.6% 0.70 448 40 推进剂B 14% 0.80 318 57 大幅度减薄 由以上结果分析认为在双基推进剂燃烧过程中有NO_2+推进剂这一气固异相反应存在。它与燃烧速度的关系密切。增速催化剂对此反应起催化作用,因而可大幅度提高燃速。平台催化剂抑制此反应,是产生平台的因素之一。两组催化剂对暗区均起催化作用。但由此而产生的暗区厚度的变化对燃烧速影响不大。

 
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