English translation for "secondary combustion"

二次燃烧

Related Translations:

combustion lag:  燃烧滞后

combustion space:  燃烧空间燃烧容积燃烧室容积

combustion starter:  燃气涡轮启动机燃烧起动器

combustion stability:  燃烧安定性燃烧安全性燃烧稳定性

combustion losses:  燃烧损失

flaming combustion:  有焰燃烧

dual combustion:  双燃

combustion time:  发动机的工作时间燃烧时间

combustion toxicology:  燃烧毒物学

combustion attemperator:  燃烧调温器

Example Sentences:

	1.	Prevention and disposal of rotary air pre - heater secondary combustion 回转式空气预热器二次燃烧的预防与处理
	2.	3 ) the secondary combustion ca n ' t affect the mixing degree and mixing efficiency between primary flow and secondary flow apparently , but the heat it ' s released can increase pressure , temperature 其中，一次流喷管主要决定了掺混的程度，而引射掺混段的构型则主要决定了掺混的效率。
	3.	In the theoretical aspect , secondary combustion in ejectorjet and thermal throat was researched . theory of duct flow was conducted , the difference and homology between heat added flow and entropy fixed flow was described 在理论研究方面，本文对引射火箭二次加热及热力喉道进行了研究，推导并分析了一般的管流理论，阐述了加热管流与变截面等熵管流之间的异同。
	4.	In consideration of computation exactness and cost , the unstructured grid , rng k - e turbulence model , renold - averaged n - s equations and second order upwind scheme were used to solve 3d turbulence flows with and without secondary combustion of a experimental strutjet rbcc in ejecting mode 在综合权衡精度和速度的基础上选取非结构网格技术、 rngk -湍流模型、雷诺平均n ? s方程、二阶上风显式离散格式求解并研究了支板式rbcc引射模态三维燃烧流场。
	5.	The dissertation accomplished the design of a fuzzy controller on the organization of the secondary combustion , how to build the fuzzy control rules , a principium design of the total fuzzy control system and a principium design of the experimental system used for accumulating inference rules 论文完成了二次燃烧组织的模糊控制器的初步设计，喷雾燃烧模糊控制规则的建立方法、步骤和整个模糊控制系统的初步设计，以及积累经验控制规则的实验系统设计。
	6.	Finally , the paper summarized all research conclusions , and proposed some reformative advices on such techniques of the rbcc secondary combustion organization , including the necessity , the feasibility and the practical value of hardware and software being migrated to a single chip in the future were also referred , so that some theoretic provisions and tech supports are offered to the investigations of rbcc 最后，本文总结了将模糊控制方法应用于rbcc二次燃烧组织方面的研究结论，并提出改进建议，包括未来将有关软、硬件系统移植到单片机上的必要性、可行性和实际价值等等。论文的工作将为rbcc燃烧组织的进一步纵深研究提供一定的理论准备和技术支持。
	7.	In the thesis , the combustions ( ejector ' s first combustion and ramjet ' s secondary combustion ) organization of a typical structure of rbcc jet ? strutjet , was studied and analyzed , to get a better and dynamic method , to organize such kind of combustions 论文从rbcc发动机的一种典型结构- - - -支板引射火箭发动机( strutjet )出发，分析了这种组合发动机的燃烧(引射火箭的一次燃烧与冲压补燃室中的二次燃烧)组织，获得了组织这类燃烧的较好方法?实时、动态的智能组织。
	8.	But the real performance can be obtained is mainly determined by the ejected secondary mass flow rate , the mixing degree , the mixing efficiency , and the secondary combustion efficiency can be obtained . 2 ) the ejected secondary mass flow rate , the mixing degree and the mixing efficiency are synthetically affected by the configuration of rbcc engine , especially the mixer and the primary nozzle , in which the primary nozzle , including shape , number and distribution mainly determines the mixing degree ; while the mixer configuration primarily determines the mixing efficiency 而实际能达到的性能则取决于实际的引射比及两种流体的实际掺混程度、掺混效率和二次燃烧效率； 2 )引射发动机的构型，包括后体及一次流喷管的形状、数量、配置等，对引射进来的二次流量、一次流和二次流之间的掺混程度和掺混效率起着主要作用。
	9.	The effects of such elements as primary flow total pressure , flow rate , degree of fuel rich , nozzle structure , flying speed and secondary combustion on ejecting mode performance were researched . it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0 . 7 . to deeply analyze thrust augmentation mechanism in low speed range , the research was further continued by changing secondary combustion organization and aft - body configuration 研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响，发现实验样机构型在0 . 7ma以上的飞行条件下可以获得推力增强，而在0 . 7ma以下无推力增强。
	10.	The effect of secondary fuel nozzle location , the mass flow rate of secondary fuel and outlet area of ejectorjet were studied . the main results are : the geometry structure of ejectorjet can be compatible with other rbcc operation modes by secondary combustion organization ; the distribution of secondary fuel on ejectorjet cross section is significant for secondary combustion stability . spi combustion organization method is promising 实验研究了二次燃料喷注位置、二次燃料喷注量、后体出口面积对引射火箭性能的影响，得到的结论为：通过燃烧组织，引射火箭模态可以和其他工作模态(亚燃超燃)共用燃烧室而不需做大的几何变化；二次燃料在引射火箭通道截面上的分布对于引射火箭的稳定工作有重要意义。

Similar Words：

"secondary color weakness" English translation, "secondary colors" English translation, "secondary colour" English translation, "secondary colour correction" English translation, "secondary combustible" English translation, "secondary combustion air" English translation, "secondary combustion zone" English translation, "secondary common pilot channel" English translation, "secondary community" English translation, "secondary compartment line" English translation