| 高来流马赫数单列叶栅改串列叶栅性能对比试验 |
| |
| 引用本文： | 向宏辉,葛宁,侯敏杰,马昌友,杨荣菲,杨泳.高来流马赫数单列叶栅改串列叶栅性能对比试验[J].航空动力学报,2016,31(11):2757-2764. |
| |
| 作者姓名： | 向宏辉 葛宁 侯敏杰 马昌友 杨荣菲 杨泳 |
| |
| 作者单位： | 1. 南京航空航天大学能源与动力学院,南京210016;中国航空发动机集团有限公司中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703;2. 南京航空航天大学能源与动力学院,南京,210016;3. 中国航空发动机集团有限公司中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油,621703;4. 中国民航飞行学院飞行技术学院,四川广汉,618307 |
| |
| 基金项目： | 江苏省普通高校研究生科研创新计划项目（KYLX15_0260） |
| |
| 摘 要： | 基于某高负荷轴流风扇高临界来流马赫数静叶改型设计的需求,对原型单列叶栅和改型串列叶栅开展性能对比试验研究,通过详细分析两型叶栅内部流场参数,量化评估了串列叶栅在高来流马赫数条件下的改进设计效果.结果表明:串列叶栅比单列叶栅在降低流动损失,提升增压能力方面具有显著优势.相比单列叶栅,设计状态下串列叶栅总压损失系数降低了19％,静压比提高了3.1％,基本缓解了单列叶栅原有设计状态的流动堵塞现象.串列叶栅前排叶片对后排叶片吸力面附面层发展会产生抑制作用,使得后排叶片具有较好的工作性能.
|
| 关 键 词： | 单列叶栅 串列叶栅 总压损失系数 静压比 等熵马赫数 |
| 收稿时间： | 2016/1/25 0:00:00 |
Performance contrast experiment of prototype single cascade and redesign tandem cascade at high inlet Mach number |
| |
| XIANG Hong-hui,GE Ning,HOU Min-jie,MA Chang-you,YANG Rong-fei and YANG Yong.Performance contrast experiment of prototype single cascade and redesign tandem cascade at high inlet Mach number[J].Journal of Aerospace Power,2016,31(11):2757-2764. |
| |
| Authors: | XIANG Hong-hui GE Ning HOU Min-jie MA Chang-you YANG Rong-fei and YANG Yong |
| |
| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Key Laboratory on Aero-engine Altitude Simulation Technology, China Gas Turbine Establishment, Aero Engine(Group) Corporation of China, Jiangyou Sichuan 621703,College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Key Laboratory on Aero-engine Altitude Simulation Technology, China Gas Turbine Establishment, Aero Engine(Group) Corporation of China, Jiangyou Sichuan 621703,Key Laboratory on Aero-engine Altitude Simulation Technology, China Gas Turbine Establishment, Aero Engine(Group) Corporation of China, Jiangyou Sichuan 621703,College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China and Department of Flight Technology, Civil Aviation Flight University of China, Guanghan Sichuan 618307, China |
| |
| Abstract: | Based on the redesign requirement of stator blade with high critical inlet Mach number of a highly-loaded axial flow fan, the performance contrast experiment of prototype single cascade and redesign tandem cascade was presented. The improvement effect of tandem cascade at high inlet Mach number was also evaluated by analyzing the internal flow field parameters of both types of cascade.Results show that the tandem cascade has significant advantages in reducing flow loss and increasing compression capacity than the single cascade. Compared with the single cascade, the total pressure loss coefficient and the static pressure ratio of the tandem cascade reduced by 19% and enhanced by 3.1%, respectively. Accordingly, the flow blockage phenomena of the single cascade at original design condition are eased basically. The front blade can restrain the boundary layer development on suction surface of the rear blade of the tandem cascade, thus the rear blade has good operating performance. |
| |
| Keywords: | single cascade tandem cascade total pressure loss coefficient static pressure ratio isentropic Mach number |
| 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 |
|
