基于容腔动力学的涡喷发动机部件级建模方法
详细信息 查看官网全文
- 英文论文题名：The Method of Component-Level Model for Turbine Engine Based on Volume Dynamics
- 论文作者：李娜 ; 谢清明 ; 牟春晖
- 英文论文作者：LI Na ; XIE Qing-ming ; MU Chun-hui ; Beijing Power Machinery Institute
- 年：2016
- 作者机构：北京动力机械研究所;
- 论文关键词：涡喷发动机 ; 容腔动力学 ; 部件模型
- 英文论文关键词：Turbine engine ; Cavity dynamics ; Model based on Component level
- 会议召开时间：2016-08-17
- 会议录名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议论文集
- 语种：中文
- 分类号：V235.11
- 学会代码：HTDZ
- 会议名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议
- 会议地点：中国陕西西安
- 主办单位：中国航天第三专业信息网、中国航天科技集团公司科技委、中国航天科工集团公司科技委
- 学会名称：中国航天第三专业信息网
- 页数：12
- 文件大小：1438k
- 原文格式：D
- 会议级别：全国
摘要
本文主要介绍了基于转子动力学、容腔动力学特性建立的涡喷发动机部件级模型的方法,避免了传统迭代法求解非线性方程组对初值依赖强,不易全包线收敛的问题。首先引入容腔动力学描述来平衡部件参数,通过容腔辅助变量的方式封闭系统状态方程,完成发动机动态模型的非迭代求解;接着将发动机模型的核心模块采用标准C语言进行代码编写,通过S函数进行封装,实现基于非图形化C语言描述系统与Simulink环境的高速混合仿真;最后将模型输出与试验数据进行对比,结果表明:所建立的模型具有较高精度,可以准确捕捉涡喷发动机的动态响应和稳态响应。
This paper obtained that the method of the component level model for turbine engine was built based on rotor dynamics points and volume dynamics, avoiding the problems including that traditional iteration is solving the nonlinearity equation set is dependent on powerfully to the initial value, and the full envelope is constriction hardly. Firstly,several variable and equations of volume dynamics in turbine engine are introduced as complementary variables and equations, and as a result, the whole set of equations becomes closed form and can be solved without iteration. Nucleus module of engine model based on C-language was programmed to S-function, executing hybrid simulation at a high speed based on non- figure C-language description system. Lastly, comparing to experimental data, the simulation results show that the model has higher precision to caputured accurately dynamic and steady state responses of turbine engine and the model can well reflect steady state and dynamic property and haves higher accuracy.
This paper obtained that the method of the component level model for turbine engine was built based on rotor dynamics points and volume dynamics, avoiding the problems including that traditional iteration is solving the nonlinearity equation set is dependent on powerfully to the initial value, and the full envelope is constriction hardly. Firstly,several variable and equations of volume dynamics in turbine engine are introduced as complementary variables and equations, and as a result, the whole set of equations becomes closed form and can be solved without iteration. Nucleus module of engine model based on C-language was programmed to S-function, executing hybrid simulation at a high speed based on non- figure C-language description system. Lastly, comparing to experimental data, the simulation results show that the model has higher precision to caputured accurately dynamic and steady state responses of turbine engine and the model can well reflect steady state and dynamic property and haves higher accuracy.
引文
[1]王继业.微型涡喷发动机控制规律研究,[D].南京:南京航空航天大学,2006.
[2]Alattab KA,Zainal ZA.Turbine Startup Methods for Externally Fired Micro Gas Turbine(EFMGT)System using Biomass Fuels.Applied Energy,2010,87:1336-1341.
[3]P.A.Pilavachi.Mini and micro-gas turbines for combined heat and power[J].Applied Thermal Engineering,2002,22:2003-2014.
[4]孙健国.现代航空动力装置控制(第二版)[M].北京:国防工业出版社,2009:138-153.
[5]樊思齐,李华聪,樊丁等.航空发动机控制[M].西安:西北工业大学出版社,2008:146-157.
[6]申涛.微型涡喷发动机建模与控制研究,[D].南京:南京航空航天大学,2011.
[7]孙健国,现代航空动力装置控制[M],南京航空航天大学,2001.4.
[8]王琴芳,航空燃气涡轮发动机原理[M],南京航空航天大学,2006.8.
[9]陈毅.航空发动机控制系统传感器故障诊断研究,[D],南京,南京航空航天大学,2007.
[10]牟春阳,李世中.基于容腔动力学的分排涡扇发动机动态建模[J].《制造业自动化》,2015.37(4).104-123.
[11]杨刚,孙健国,黄向华,等.一种不需要迭代的发动机辅助变量建模方法[J].航空动力学报,2003,18(2):289-294.
[12]陶金伟.航空发动机组态建模仿真技术研究[D].南京:南京航空航天大学,2009.12.
[13]邹先权.涡轴发动机自适应模型的建立与鲁棒控制[D].南京:南京航空航天大学,2008.12.
[14]于龙江,朴英.一种简化算法的航空发动机全状态数学模型[J].航空动力学报,2008,23(3):510-515.
[15]王正林.MATLAB/Simulink与控制系统仿真,[M].北京:电子工业出版社,2008:67-82.
[16]夏超,王继强,商国军,等.基于Matlab/Simulink的航空发动机部件级建模与分析[J].航空发动机,2012,38(4):31-33.
[2]Alattab KA,Zainal ZA.Turbine Startup Methods for Externally Fired Micro Gas Turbine(EFMGT)System using Biomass Fuels.Applied Energy,2010,87:1336-1341.
[3]P.A.Pilavachi.Mini and micro-gas turbines for combined heat and power[J].Applied Thermal Engineering,2002,22:2003-2014.
[4]孙健国.现代航空动力装置控制(第二版)[M].北京:国防工业出版社,2009:138-153.
[5]樊思齐,李华聪,樊丁等.航空发动机控制[M].西安:西北工业大学出版社,2008:146-157.
[6]申涛.微型涡喷发动机建模与控制研究,[D].南京:南京航空航天大学,2011.
[7]孙健国,现代航空动力装置控制[M],南京航空航天大学,2001.4.
[8]王琴芳,航空燃气涡轮发动机原理[M],南京航空航天大学,2006.8.
[9]陈毅.航空发动机控制系统传感器故障诊断研究,[D],南京,南京航空航天大学,2007.
[10]牟春阳,李世中.基于容腔动力学的分排涡扇发动机动态建模[J].《制造业自动化》,2015.37(4).104-123.
[11]杨刚,孙健国,黄向华,等.一种不需要迭代的发动机辅助变量建模方法[J].航空动力学报,2003,18(2):289-294.
[12]陶金伟.航空发动机组态建模仿真技术研究[D].南京:南京航空航天大学,2009.12.
[13]邹先权.涡轴发动机自适应模型的建立与鲁棒控制[D].南京:南京航空航天大学,2008.12.
[14]于龙江,朴英.一种简化算法的航空发动机全状态数学模型[J].航空动力学报,2008,23(3):510-515.
[15]王正林.MATLAB/Simulink与控制系统仿真,[M].北京:电子工业出版社,2008:67-82.
[16]夏超,王继强,商国军,等.基于Matlab/Simulink的航空发动机部件级建模与分析[J].航空发动机,2012,38(4):31-33.