| 进气畸变对变循环发动机气动稳定性影响分析模型 |
| |
| 引用本文： | 严伟,胡骏,屠宝锋,张晨凯,尹超.进气畸变对变循环发动机气动稳定性影响分析模型[J].航空动力学报,2015,30(11):2680-2687. |
| |
| 作者姓名： | 严伟 胡骏 屠宝锋 张晨凯 尹超 |
| |
| 作者单位： | 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016 |
| |
| 基金项目： | 高等学校博士学科点专项科研基金(20113218120006) |
| |
| 摘 要： | 为了预估变循环发动机气动稳定性对周向进气畸变的响应,建立了进气畸变对变循环发动机气动稳定性影响分析模型.采用带源项的二维非定常欧拉方程描述变循环发动机内部的流动,根据部件特性计算源项,采用时间推进法求解方程组.利用该模型分析了周向进气畸变沿某变循环发动机流路的传递和该发动机的临界畸变指数,计算结果表明:该模型实现了对进气畸变影响变循环发动机气动稳定性的仿真;进气畸变经过核心机驱动风扇级后有显著的衰减;核心机驱动风扇级对进气畸变非常敏感,易发生失稳,是变循环发动机抗畸变的薄弱点.
|
| 关 键 词： | 进气畸变 变循环发动机 气动稳定性 核心机驱动风扇级 分析模型 |
| 收稿时间： | 2014/4/22 0:00:00 |
Analytical model of inlet distortion effect on aerodynamic stability of variable cycle engine |
| |
| YAN Wei,HU Jun,TU Bao-feng,ZHANG Chen-kai and YIN Chao.Analytical model of inlet distortion effect on aerodynamic stability of variable cycle engine[J].Journal of Aerospace Power,2015,30(11):2680-2687. |
| |
| Authors: | YAN Wei HU Jun TU Bao-feng ZHANG Chen-kai and YIN Chao |
| |
| Institution: | Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China and Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| |
| Abstract: | A theoretical model was established to assess the effect of circumferential inlet distortion on the aerodynamic stability of the variable cycle engine. The model incorporated source items into the two-dimensional unsteady Euler's equations to describe the flow through variable cycle engine. The source items were calculated according to the component characteristic and the equations were solved by time-advancing method. The circumferential inlet distortion transfer curve along the flow path and the critical distortion factor of the variable cycle engine were obtained. The results suggest that the model accomplishes the simulation of inlet distortion effect on aerodynamic stability of variable cycle engines. The inlet distortion experiences a great attenuation when passing through the core driven fan stage. The core driven fan stage is sensitive to distortion. It is the weakest link of the aerodynamic stability of the variable cycle engine. |
| |
| Keywords: | inlet distortion variable cycle engine aerodynamic stability core driven fan stage analytical model |
| 本文献已被 CNKI 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 |
|
