| 民用涡扇发动机起动过程改进的分段组合控制计划研究与试验 |
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| 引用本文： | 孔祥兴,王曦,张绍基,尹长志,王祥宇.民用涡扇发动机起动过程改进的分段组合控制计划研究与试验[J].航空动力学报,2014,29(12):2924-2929. |
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| 作者姓名： | 孔祥兴 王曦 张绍基 尹长志 王祥宇 |
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| 作者单位： | 中国航空工业集团公司 中航空天发动机研究院有限公司, 北京 100028;北京航空航天大学 能源与动力工程学院, 北京 100191;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015;中国航空工业集团公司 中航空天发动机研究院有限公司, 北京 100028;中国航空工业集团公司 中航空天发动机研究院有限公司, 北京 100028 |
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| 摘 要： | 针对某型民用涡扇发动机,将n-dot闭环控制算法应用于涡扇发动机起动过程,设计了涡扇发动机起动过程开环与闭环分段组合的控制计划,仿真表明:涡扇发动机起动过程采用n-dot闭环控制算法在初始阶段会出现参数摆动的情况.为此,基于油气比作控制变量进行消喘的原理,对n-dot闭环控制算法进行了改进,以消除起动初始阶段的参数摆动.试验结果表明:改进后的分段组合的控制计划能够有效抑制参数摆动现象;并且,对于不同大气条件的起动测试,起动过渡态过程高压转子转速的数值差距不大于1.0%,延时不超过0.9s;而对于不同飞行状态的起动测试,起动过渡态过程高压转子转速的数值差距不大于1.0%,延时不超过1.2s,具有良好的稳定性和重复性.
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| 关 键 词： | n-dot闭环控制 闭环控制 自适应控制 起动控制规律 涡扇发动机 |
| 收稿时间： | 2013/7/29 0:00:00 |
Research and experiment on improved sectional combination control scheme for civil turbofan engine's startup process |
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| KONG Xiang-xing,WANG Xi,ZHANG Shao-ji,YIN Chang-zhi and WANG Xiang-yu.Research and experiment on improved sectional combination control scheme for civil turbofan engine''s startup process[J].Journal of Aerospace Power,2014,29(12):2924-2929. |
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| Authors: | KONG Xiang-xing WANG Xi ZHANG Shao-ji YIN Chang-zhi and WANG Xiang-yu |
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| Affiliation: | Academy of Aeronautic Propulsion Technology, Aviation Industry Corporation of China, Beijing 100028, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Academy of Aeronautic Propulsion Technology, Aviation Industry Corporation of China, Beijing 100028, China;Academy of Aeronautic Propulsion Technology, Aviation Industry Corporation of China, Beijing 100028, China |
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| Abstract: | A n-dot closed loop control algorithm was applied to the startup process for a civil turbofan engine. Therefore, an openned/closed loop sectional combination control scheme for turbofan engine's starup process was designed. The simulation result shows that the n-dot closed loop control algorithm could cause oscillation at the beginning of startup process of turbofan engine. To eliminate the parameters' oscillation at the beginning of startup process, the n-dot closed loop control algorithm was improved according to the rationale of surge recovery by using fuel air ratio unit as the control variable. The experiment results illustrate that the improved sectional combination control scheme could effectively restraine the parameters' oscillation, and furthermore the startup transition process had satisfying stability and repetitive. The numerical difference of high pressure rotor speed under different atmosphere conditions does not exceed 1.0% and the time delay does not exceed 0.9s; meanwhile the numerical difference of high pressure rotor speed under different flight conditions does not exceed 1.0% and the time delay does not exceed 1.2s. |
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| Keywords: | n-dot closed loop control closed loop control adaptive control startup control law turbofan engine |
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