|
|||||
|
|
| 某型航空涡轴发动机整机吞水性能试验 | |
| 引用本文： | 旷桂兰,王道波,单晓明,吴志勇,韦海龙.某型航空涡轴发动机整机吞水性能试验[J].航空动力学报,2009,24(11):2415-2420. |
| 作者姓名： | 旷桂兰 王道波 单晓明 吴志勇 韦海龙 |
| 作者单位： | 1. 南京航空航天大学,能源与动力学院,南京,210016;中国航空工业集团公司,中国航空动力机械研究所,株洲,412002 2. 南京航空航天大学,自动化学院,南京,210016 3. 中国航空工业集团公司,中国航空动力机械研究所,株洲,412002 |
| 摘 要： | 为进行某型航空涡轴发动机吞水试验,设计了喷水设备及专用进气整流装置,采用大小喷水环实现对发动机进行给定水流量的喷入.进行了发动机进口吞水量为空气流量2.5%和3.5%的试验,试验结果表明:试验方法及装置的设计合理可行;均匀吞水量不高于进气流量3.5%,发动机吞水时各截面温度下降量由进口至出口依次降低;吞水试验后,发动机性能下降. |
| 关 键 词： | 航空发动机 吞水试验 测试 流量 喘振 |
| 收稿时间： | 2008/11/12 0:00:00 |
| 修稿时间： | 2009/1/11 0:00:00 |
Swallowing water capability experiment of one turbine-shaft overall aviation engine |
|
| KUANG Gui-lan,WANG Dao-bo,SHAN Xiao-ming,WU Zhi-yong and WEI Hai-long.Swallowing water capability experiment of one turbine-shaft overall aviation engine[J].Journal of Aerospace Power,2009,24(11):2415-2420. | |
| Authors: | KUANG Gui-lan WANG Dao-bo SHAN Xiao-ming WU Zhi-yong and WEI Hai-long |
| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou 412002, China;College of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou 412002, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou 412002, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou 412002, China |
| Abstract: | Waterworks and special air intake path were designed to conduct swallowing water experiments for one aviation turbine-shaft engine under research,while big and small rings were used to spurt certain quantity of water into the engine.The experiments were conducted at swallowing water in the quantity of 2.5% and 3.5% of engine's intake air.The results show that,the designs of the experiment method and device are feasible;when symmetrically swallowing water not higher than 3.5% of engine's intake air,the temperature drop at each engine's section decreases from the inlet to the exit;the engine's performance degrades after swallowing water experiments. |
| Keywords: | aviation engine swallowing water experiment test flux surge |
| 本文献已被 万方数据 等数据库收录！ | |
| 点击此处可从《航空动力学报》浏览原始摘要信息 | |
| 点击此处可从《航空动力学报》下载免费的PDF全文 | |