| 1. | Some propellant droplets may not evaporate within the confines of the thrust chamber .
有些推进剂可能在推力室内并未汽化。 |
| 2. | One approach consists of varying only the total flow thereby maintaining the same thrust chamber hardware .
有一种方法是仅改变推进剂总流量，而推力室结构保持不变。 |
| 3. | Heat transfer characteristics of platelet transpiration - cooling thrust chamber
多斜孔层板发散冷却流动传热特性 |
| 4. | Heat transfer in four parallel connecting thrust chambers with radiation cooling was analyzed
摘要分析了四机?联全辐射冷却推力室的热特点。 |
| 5. | Also , the analysis of the system with only one pair of operating thrust chambers was performed
对仅有两对角推力室工作、另一对推力室不工作时的温度分布特点也作了分析。 |
| 6. | As to the simulation , the inner flow field of thrust chamber was simulated . here the thrust chamber was treated as a two - dimension problem . the simulation model involved injection , mixing and combustion of gaseous propellant
仿真方面，对三组元发动机推力室的稳态燃烧过程进行了数值模拟，分析了推进剂各组元和各燃烧产物组分在推力室内的分布。 |
| 7. | The energy equation of the thrust chamber wall was developed by omitting radical heat conduction and only considering the radiation heat transfer of the four chambers , the radiation leakage through nozzle exit , the axial and circular heat conduction
忽略径向导热，考虑推力室外向的相互及自身辐射交换、内壁经喷口的辐射泄漏以及周向和轴向的传导热量，建立了推力室壁的能量方程。 |
| 8. | Focusing on the performance evaluating and the design of tripropellant injector , adopting the cold test rig with background pressure supply , malvem particle analyzer , ccd photography system , tripropellant hot test - bed , numerical simulation software and auxiliary theoretical a nalysis , the d ischarge c haracteristic a s w ell a s a tomization p erformance o f the injector and the combustion performance as well as the mode - transition characteristic of thrust chamber are studied detailedly based on the 3 different structures of coaxial tripropellant injector , large numbers of important conclusions are gained
本文围绕三组元喷嘴的性能评定及设计方法。采用反压冷试台、马尔文测粒仪、 ccd高速摄影系统、三组元发动机热态试验台、数值仿真程序及辅助理论分析等多种技术手段和研究方法，对三种结构的同轴式三组元喷嘴深入进行了喷嘴流量特性和雾化特性、推力室燃烧性能和转工况性能研究，得到了大量重要结果。 |
| 9. | Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles , such as thrust chamber and turbine rotor of launch rock et engine , titanium tube of satellite , attitude control engine injector and wave guide component of satell ite , reflector , tube and honeycomb panel of manned spacecraft , main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n
文摘:简略地介绍了先进钎焊技术在航天器部件，例如运载火箭发动机的推力室和涡轮转子、人造卫星的钛导管、姿控发动机喷注器和波导器件、载人飞船的反射器、导管和蜂窝壁板、航天飞机的主发动机喷管和预燃室以及空间站的管路系统等的广泛应用情况。 |
| 10. | The channel scale on transpiration cooling for the platelet thrust chamber of liquid propellant rocket engine is approaching micron dimension . it is very possible that micro - scale effects will occur in the flow and heat transfer of the channel . in the past , researchs on flow and heat transfer in the platelet micro - channel are mostly based on macro - scale theory
液体火箭发动机推力室壁面发汗冷却通道的尺度已达微米量级,通道内的流动与换热很可能存在微尺度效应,以前的相关研究都以宏观尺度的理论为依据,其研究结果的合理性需要进行微尺度效应的分析。 |
