| 1. | Performance analysis for irreversible combined heat engine cycle with supplemental combustion
补燃型不可逆联合循环热机的性能分析 |
| 2. | Contrast study on cold - flow mixing effect and combustion efficiency of afterburning chamber of solid rocket ramjet
固冲发动机补燃室冷流掺混效果与燃烧效率对比研究 |
| 3. | Performance analysis for a combined carnot and rankine heat engine cycle with heat resistance , heat leakage and supplemental combustion
热漏和补燃的卡诺和朗肯联合热机循环性能分析 |
| 4. | It is a key technique for ducted rocket to make the second combustor operate at high efficiency and stability
实现补燃室高效率、稳定、可靠的工作，是固体火箭冲压发动机的关键技术问题。 |
| 5. | The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet
超声速进气道及补燃室的设计与性能研究是固体火箭冲压发动机的两大关键技术。 |
| 6. | The process of mixing and chemical reaction in the second combustor is very complicated , many factors affect the combustion efficiency
然而补燃室内燃气同空气的掺混燃烧过程十分复杂，影响燃烧效率的设计参数很多。 |
| 7. | The performance of supersonic inlet determines the pressure and the air flux in combustor , then affect the work of ramjet
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量,进而影响到冲压发动机的工作性能。 |
| 8. | During the study of solid rocket ramjet ( srr ) , ablation of afterburner thermal insulation is a serious problem , which cannot be ignored
固冲发动机补燃室绝热层的烧蚀问题是目前固冲发动机研制过程中所面临的一个重要问题。 |
| 9. | The calculating procedure that ethanol ( c2h6o ) reacting with hydrogen peroxide ( h2o2 ) was deduced based on chemical theory and characters of c2h6o and h2o2
摘要介绍了过氧化氢催化分解气体加酒精补燃以提高气体发生器排气温度的理论计算和分析方法，并建立了一套实验研究装置。 |
| 10. | For studying the performance of solid rocket ramjet under the influence of different flight conditions , it ' s significant to simulate the integrated flow field of inlet and combustor
因此,开展超声速进气道/补燃室流场一体化数值模拟研究对于考查飞行状态对于火箭冲压发动机性能的直接影响具有重要的现实意义。 |
