| 基于双火花塞点火策略的活塞式航空煤油发动机爆震控制 |
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| 引用本文： | 刘娜,宋玺娟,胡春明,王赫. 基于双火花塞点火策略的活塞式航空煤油发动机爆震控制[J]. 航空动力学报, 2019, 34(8): 1671-1676. DOI: 10.13224/j.cnki.jasp.2019.08.005 |
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| 作者姓名： | 刘娜 宋玺娟 胡春明 王赫 |
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| 作者单位： | 天津大学内燃机研究所,天津,300072;天津大学内燃机研究所,天津300072;天津大学机械工程学院,天津300072;天津大学机械工程学院,天津,300072 |
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| 基金项目： | 国家自然科学基金面上项目(51476112) |
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| 摘 要： | 在一台650 mL单缸活塞式航空发动机上,针对双火花塞点火方式对活塞式航空煤油发动机的爆震控制进行了试验研究。结果表明:采用两个火花塞同步点火,且将点火提前角推迟可以有效的抑制爆震,同时燃烧放热率幅值逐渐降低,整体燃烧相位逐渐推迟;采用双火花塞异步点火随着点火提前角点火相位差的增加,爆震强度逐渐降低,通过匹配主火花塞点火提前角与副火花塞点火提前角可进一步提升发动机的动力性。
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| 关 键 词： | 爆震控制 航空煤油 点火提前角 双火花塞 活塞式航空发动机 |
| 收稿时间： | 2019-01-05 |
Knocking control of piston-type aviation kerosene engine based on dual-spark plug ignition strategy |
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| Abstract: | Focusing on dual-spark plug ignition forms, test studies were conducted on a 650 mL piston-type single engine using kerosene as fuel. Result showed that the ignition advance angle of dual spark plug synchronous ignition delay can effectively restrain detonation, meanwhile, the amplitude of combustion heat release rate decreased gradually, and the whole combustion phase was delayed gradually. With the increase of ignition phase difference of ignition advance angle, the knock intensity decreased gradually. By matching the ignition advance angle of the major spark plug with the ignition advance angle of the auxiliary spark plug, the power performance of the engine can be further improved. |
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| Keywords: | knocking control aviation kerosene ignition advance angle dual-spark plug piston aviation engine |
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