片语

burning-rate coefficient燃烧速率系数

burning-rate accelerator助燃剂

burning g rate燃烧速率

high burning-rate高燃速

burning-rate constant[热]

catalytic burning-rate燃速催化性能

burning loss rate烧损率

firing rate射速；燃料用量；燃烧率，燃烧速度

combustion rate[热] 燃烧率；[热] 燃烧速度

Ti Burning Loss RateTi烧损率

英汉例句

• A method suitable for calculating the burning rate of combustible gas in CFBC has been created.

  建立了一种适合于循环流化床燃烧室(CFBC)条件下可燃气体的燃烧计算方法。

• For the propellant mechanism of increasing burning rate is discussed.

  分析了这种推进剂能提高燃速的机理。

• A laser method was used for measuring transient burning rate delay of solid propellant in oscillatory combustion.

  应用激光方法测量压力振蕩过程中的固体推进剂瞬态燃速。

• It is shown that with the content of CB raised, the burning rate of the propellant is increased and their plateau (or mesa) zone translate into higher pressure;

  指出随着炭黑含量的增加，推进剂燃速也增加，平台或麦撒燃烧区向高压移动；

• The neural network is adopted to study the burning rate identification of the solid fuel ramjet.

  用神经网络技术对固体燃料沖压动机的燃速辨识问题进行了研究。

• The burning rate of the fuel-rich propellants is the parameter which is important for Ducted Rocket design and performance analysis and is main inspection criterions of propellant prescriptions.

  贫氧推进剂燃速是固体火箭沖压发动机设计和性能分析的重要参数，也是对推进剂配方进行检验验收的主要指标。

• Burning rate measurement with closed burner is a rapid method for measuring burning rate character and its change of solid rocket propellants in a wide pressure range.

  密闭燃烧器法是一种能测定很宽压强范围内固体火箭推进剂燃速特性及变化情况的快速测量方法。

• The difference of the burning peculiarity between propellants whose boron was coated with and without AP was compared by measuring the explosive heat and burning rate of the propellants.

  并测量了推进剂的爆热和燃速，比较了AP包覆硼粒子对推进剂燃烧性能的影响。

• Among those methods to improve the burning rate of solid propellant, the nanometer-sized catalyst has been considered as one kind of most prospective methods.

  在提高固体推进剂燃速的众多方法中，采用纳米催化剂被认为是最有前途的方法之一。

• Applying burning-rate catalysts is one of optimal approaches to regulate the burning rate of HTPB propellant.

  使用燃速催化剂是调节丁羟推进剂燃速的最佳途径之一。

• Twin screw extrusion technology of porous ultra high burning rate propellant (UHBRP) substitutes was studied.

  研究了多孔超高燃速推进剂代料的双螺桿混合挤出工艺。

• Based on the results of tests, the relationship between burning rate augmentation and burning time is discussed. A physical model is also presented and studied.

  根据试验结果，论述了燃速增加率与燃烧历程的关系，提出和探讨了燃烧物理模型问题。

• The static burning rate of cigarette is first increased, continuously come up to a 「peak value」, and then let up while the dosage of burning accelerant is increased.

  在相同的实验条件下，卷烟的自由燃烧速度随助燃剂添加量的增加呈先增大后减小的变化规律。

• Variety of the burning rate pressure exponent will give expression to the additive「s catalysis to the propellant」s combustion.

  燃速压力指数的变化情况说明了催化剂对燃烧所起催化作用的大小。

• Thus, improving the condensed-phase reaction can increase of the burning rate for fuel-rich propellant with boron in low pressure condition.

  分析表明促进凝相反应有利于含硼富燃料推进剂低压燃速的提高。

• The combustion of hydrogen in coke under regeneration is also discussed and its relative burning rate is reckoned.

  讨论了在催化裂化再生器中焦中氢元素的燃烧，并推算出其相对燃烧速度。

• The pressure in cylinder will stabilize quicker under low rotate speed. When turbulent intensity was increasing, the instantaneous burning rate will also increase and get better thermal efficiency.

  湍流强度的增大可以提高瞬时的燃烧率，缩短燃烧持续期，从而提高了发动机的热效率。

• The results of the burning rate measurement showed that the nanometer sized lead oxide can play a role in decreasing the pressure exponent of NEPE propellant.

  通过纳米氧化铅在NEPE推进剂中的实际应用效果表明：纳米氧化铅可有效的降低NEPE推进剂的燃速压力指数。

• Catalyst of the organo-metallic compound (OME) on the combustion and thermal decomposition of HNIW monopropellant was investigated through burning rate measurement, DSC and TG thermal analysis.

  通过燃速测定、差示扫描量热技术(dsc)和热失重技术(TG)研究了有机金属化合物催化剂(ome)对六硝基六氮杂异伍兹烷(HNIW)单元推进剂热分解和燃烧性能的影响。

• The approximate analytical solution on the burning rate of droplet mass is also found on the basis of some simplified hyPotheses.

  在一些简化假设的基础上，找到了液滴质量燃速的近似解析解。

• The results of tests show that the burning rates of uncured propellants can be predicated exactly with DSC method and the base burning rate of some formulation is predicated successfully.

  实验结果表明，用DSC法可较準确地预示未固化推进剂的燃速，并成功预示了某配方的基础燃速。

• The effect of hydrogen on methane combustion and ignition temperature, burning rate and burnout time are discussed through analyzing the calculated results.

  通过分析计算，讨论了氢气对甲烷燃烧过程及着火温度、燃烧速率、燃尽时间的影响。

• An application investigation of the nitramine (RDX, HMX) to the low burning rate HTPB propellants was carried out in the view of energetic property and combustion performance.

  从推进剂的能量特性和燃烧性能的角度探索了硝胺(rdx、HMX)在低燃速丁羟推进剂应用的可能性。

• The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated.

  研究了过渡金属氧化物（TMO ）及其复配物对非壅塞固体火箭沖压发动机铝镁贫氧推进剂燃烧特性的影响。研究发现，氧化铁对提高铝镁贫氧推进剂燃速的作用显着。