毫米级微型涡轮发动机性能仿真模型

刘传凯; 李艳茹

doi:10.13700/j.bh.1001-5965.2017.0566

毫米级微型涡轮发动机性能仿真模型

doi: 10.13700/j.bh.1001-5965.2017.0566

刘传凯^{1, 2, ,},
李艳茹³

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

基金项目:

国防基础科研项目 B2120132006

详细信息

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

通讯作者:
刘传凯.E-mail:liuchuankai@buaa.edu.cn

中图分类号: V228.3
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- 被引次数: 0
出版历程
- 收稿日期: 2017-09-08
- 录用日期: 2018-01-26
- 网络出版日期: 2018-07-20

Performance simulation model of millimeter-scale micro turbine engine

LIU Chuankai^{1, 2
, ,},
LI Yanru³

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

Funds:

National Defense Basic Research Program B2120132006

More Information

Corresponding author: LIU Chuankai.E-mail:liuchuankai@buaa.edu.cn

摘要

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。
- 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.
- micro-engine /
- thermal network method /
- performance model /
- zero-dimensional simulation /
- transient process

HTML全文

图 1 微型涡轮发动机的典型结构示意图

Figure 1. Schematic of typical structure of micro turbine engine

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图 2 转子换热路径示意图

Figure 2. Schematic of heat transfer routes of rotor

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图 3 考虑转子热平衡的微型涡轮发动机性能仿真模型示意图

Figure 3. Schematic of micro turbine engine performance simulation model considering thermal balance of rotor

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图 4 静子换热路径示意图

Figure 4. Schematic of heat transfer routes of stator

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图 5 燃烧室结构换热单元划分

Figure 5. Heat transfer element division of combustor structure

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图 6 燃烧室结构的热网络模型

Figure 6. Heat network model of combustor structure

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图 7 转速及甲烷流量的变化过程

Figure 7. Evolution of rotational speed and methane flow

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图 8 换热热流及轴功率的变化过程

Figure 8. Evolution of heat flux and shaft power

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图 9 微型涡轮发动机启动过程共同工作线

Figure 9. Startup operating line of micro-engine

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图 10 转子换热热流相对值的变化过程

Figure 10. Evolution of rotor relative heat flux

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