北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (7): 1430-1437.doi: 10.13700/j.bh.1001-5965.2017.0566

• 论文 • 上一篇    下一篇

毫米级微型涡轮发动机性能仿真模型

刘传凯1,2, 李艳茹3   

  1. 1. 北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室, 北京 100083;
    2. 先进航空发动机协同创新中心, 北京 10008;
    3. 北京航空航天大学 交通科学与工程学院, 北京 100083
  • 收稿日期:2017-09-08 出版日期:2018-07-20 发布日期:2018-07-25
  • 通讯作者: 刘传凯.E-mail:liuchuankai@buaa.edu.cn E-mail:liuchuankai@buaa.edu.cn
  • 作者简介:刘传凯 男,博士,讲师,硕士生导师。主要研究方向:航空发动机总体技术;李艳茹 女,硕士研究生。主要研究方向:毫米级微型发动机。
  • 基金资助:
    国防基础科研项目(B2120132006)

Performance simulation model of millimeter-scale micro turbine engine

LIU Chuankai1,2, LI Yanru3   

  1. 1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. Collaborative Innovation Center of Advanced Aero-Engine, Beijing 10008;
    3. School of Transportation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2017-09-08 Online:2018-07-20 Published:2018-07-25

摘要: 为满足毫米级微型涡轮发动机性能设计需求,提出了一种毫米级微型涡轮发动机性能仿真模型。该模型采用考虑低雷诺数效应和传热效应的微型涡轮发动机叶轮特性,并将热平衡方程纳入该发动机性能仿真模型的共同工作方程组。通过与静子结构热网络方程组的耦合求解,实现了微型涡轮发动机特性和部件传热的动态模拟。以典型毫米级微型涡轮发动机为对象建立了仿真算例,研究了启动过程中发动机内部参数的变化规律。结果表明:毫米级微型涡轮发动机转动惯量对其加速性能影响微小,非稳态传热效应是影响其过渡态特性的主要因素。发动机转子和静子部件达到热响应时间存在显著差异,导致发动机启动过程的工作线呈现多拐点的现象。

关键词: 微型发动机, 热网络法, 性能模型, 零维仿真, 过渡过程

Abstract: In order to meet the requirement of milimeter-scale micro turbine engine performance design, a numerical model was presented to evaluate the performance of millimeter-scale micro gas turbine engines. In this model, new turbomachinery characteristic maps were applied, which took both low Reynolds number effects and heat transfer effects into consideration. Heat balance equations were also added into the matching equations. By coupled solving of the matching equations and the static structure thermal network equations, the engine performance and component heat transfer were dynamically simulated. Furthermore, a typical millimeter-scale micro turbine engine was modeled to study the dynamic changes of the engine internal parameters during startup. The results show that the rotational inertia has little influence on engine acceleration, while the unsteady heat transfer is the major determinant of engine transient performance. There is significant difference in thermal response time between rotor and static structures, which results in several kinks in startup operating line.

Key words: micro-engine, thermal network method, performance model, zero-dimensional simulation, transient process

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发