Parameter design and application of turbofan engine nozzle feedback system
-
摘要:
为了保证涡扇发动机工作过程中喷口反馈系统的实时反馈精度，以喷口反馈系统参数的合理设计为目标，通过运动分析建立冷热态数学模型，运用Spearman秩相关系数法对喷口反馈系统参数进行敏感性分析，提出参数设计方法并通过工程应用验证。研究结果表明：喷口反馈系统工作过程中喷口喉道直径与反馈角度的关系呈线性。补偿钢索支撑点到滑轮支撑铰点的距离、滑轮支撑摇臂与反馈支撑摇臂的夹角、滑轮初始圆心到滑轮支撑铰点的距离是影响喷口反馈系统实时反馈精度的主要参数，影响程度相当。利用提出的参数设计方法，通过全局寻优，能找到保证实时反馈精度的参数最优解。将研究成果应用于某型发动机，热膨胀前后喷口喉道直径与反馈角度的线性关系一致性好（相同反馈角度时喷口喉道面积差异在0.17%以内），能够有效保证喷口反馈系统的实时反馈精度，验证了本文喷口反馈系统参数设计方法合理有效。
Abstract:In order to ensure the real-time feedback accuracy of the nozzle feedback system during the working process of the turbofan engine, the mathematical model of hot and cold states was established by motion analysis for reasonable design of the nozzle feedback system parameters, and the Spearman rank correlation coefficient method was used to analyze the sensitivity of the nozzle feedback system parameters. The method of parameter design was put forward and verified by engineering application. Results showed that the relationship between nozzle throat diameter and feedback angle was linear in the process of nozzle feedback system. The distance from the support point of the compensation to the support point of the pulley, the angle between the pulley support rocker arm and the feedback support rocker arm, and the distance from the initial center of the pulley to the pulley support hinge point constituted the main parameters affecting the real-time feedback accuracy of the nozzle feedback system, and the influence of the three parameters was similar. The optimal solution of the parameters can be found to ensure the real-time feedback accuracy of the nozzle feedback system through global optimization using the established parameter design method. The application of this research result on a certain type of aero-engine showed a high consistency of the linear relationship between the nozzle throat diameter and the feedback angle (the difference in nozzle throat area was within 0.17% at the same feedback angle), which can effectively ensure the real-time feedback accuracy of the nozzle feedback system, verifying the rationality and effectiveness of the parameter design method for the nozzle feedback system.
-
图 5 喷口反馈系统平面四连杆机构结构示意图
Figure 5. Planar four bar linkage diagram of nozzle feedback system
图 10 喷口喉道直径与反馈角度的关系曲线
Figure 10. Relation curve of nozzle throat diameter and feedback angle
图 11 $ {A}_{1} $点在坐标y、z方向受力结果
Figure 11. Stress results of point $ {A}_{1} $ in the y and z directions
图 12 $ {B}_{1} $点在坐标y、z方向受力结果
Figure 12. Stress results of point $ {B}_{1} $ in the y and z directions
图 13 $ {C}_{1} $点在坐标y、z方向受力结果
Figure 13. Stress results of point $ {C}_{1} $ in the y and z directions
图 14 $ {D}_{1} $点在坐标y、z方向受力结果
Figure 14. Stress results of point $ {D}_{1} $ in the y and z directions
图 15 喷口喉道直径与反馈角度的线性关系
Figure 15. Linear relationship of nozzle throat diameter and feedback angle
图 16 反馈钢索、补偿钢索及角位移传感器
Figure 16. Feedback cable, compensated cable and angular displacement sensor
图 18 喷口反馈系统反馈组件运动模型示意图
Figure 18. Motion model diagram of nozzle feedback system component
图 19 各参数对$ {\Delta L}_{1}-{\Delta L}_{2} $的Spearman秩相关系数
Figure 19. Spearman rank correlation coefficient of each parameters for $ {\Delta L}_{1}-{\Delta L}_{2} $
图 20 敏感参数$ {L}_{AJ} $对$ {\Delta L}_{1}-{\Delta L}_{2} $的响应面
Figure 20. Response surface of sensitive parameter $ {L}_{AJ} $ for $ {\Delta L}_{1}-{\Delta L}_{2} $
图 21 敏感参数$ \delta $对$ {\Delta L}_{1}-{\Delta L}_{2} $的响应面
Figure 21. Response surface of sensitive parameter $ \delta $ for $ {\Delta L}_{1}-{\Delta L}_{2} $
图 22 敏感参数$ {L}_{AB} $对$ {\Delta L}_{1}-{\Delta L}_{2} $的响应面
Figure 22. Response surface of sensitive parameter $ {L}_{AB} $ for $ {\Delta L}_{1}-{\Delta L}_{2} $
图 23 各参数对$ \Delta D/D $的Spearman秩相关系数
Figure 23. Spearman rank correlation coefficient of each parameters for $ \Delta D/D $
图 24 各参数对$ \Delta \mathrm{\alpha } $的Spearman秩相关系数
Figure 24. Spearman rank correlation coefficient of each parameters for $ \Delta \mathrm{\alpha } $
图 25 敏感参数$ {l}_{5} $对$ \Delta D/D $的响应面
Figure 25. Response surface of sensitive parameter $ {l}_{5} $ for $ \Delta D/D $
图 26 敏感参数$ {l}_{6} $对$ \Delta D/D $的响应面
Figure 26. Response surface of sensitive parameter $ {l}_{6} $ for $ \Delta D/D $
图 27 敏感参数$ \alpha $对$ \Delta \mathrm{\alpha } $的响应面
Figure 27. Response surface of sensitive parameter $ \alpha $ for $ \Delta \mathrm{\alpha } $
图 28 5次标定结果与数学模型分析结果对比
Figure 28. Comparison between five calibration results and mathematical model analysis results
图 29 热膨胀后喷口喉道直径与反馈角度关系
Figure 29. Relationship of nozzle throat diameter and nozzle feedback angle
表 1 参数的取值范围和初始值
Table 1. Parameters value range and initial value
设计变量 取值范围 初始值 $ {H}_{AF} $ [20, 40] 20 $ {L}_{CF} $ [55, 75] 75 $ {L}_{AB} $ [25, 45] 45 $ {R}_{1} $ [5, 25] 25 $ {R}_{2} $ [40, 55] 55 $ {L}_{AJ} $ [40, 60] 60 $ \gamma $ [0.1, 10] 10 $ \delta $ [20, 55] 55 $ {\Delta L}_{2} $ [0, 8] 7 
下载: 导出CSV
表 2 参数的取值范围和初始值
Table 2. Parameters value range and initial value
设计变量 取值范围 初始值 $ {l}_{1} $ [13, 20] 20 $ {l}_{2} $ [47, 52] 52 $ {l}_{3} $ [22, 25] 21 $ {l}_{4} $ [49, 53] 49 $ {l}_{5} $ [150, 250] 210 $ {l}_{6} $ [350, 450] 400 $ \alpha $ [−1.2, 98.8] 0
下载: 导出CSV
表 3 喷口喉道直径与反馈角度的标定对照表
Table 3. Calibration comparison table of nozzle throat diameter and nozzle feedback angle
喉道直径D/mm 反馈角度α/（°） 第1次标定 第2次标定 第3次标定 第4次标定 第5次标定 485 0 0 0 0 0 519 13.3 14 13.8 13.5 13.6 600 43.3 43 43.3 43.1 43.5 650 60.2 60.5 60.8 60.5 61 750 93 92.5 92.6 92.3 92.5
下载: 导出CSV
表 4 5次标定反馈角度与数学模型分析对比
Table 4. Comparison between five calibration feedback angles and mathematical model analysis results
喷口喉道
直径D/mm数学模型分析 5次标定结果 α 偏差 α1 平均偏差/% 485 0 基准 0 0 519 13.6 14 0.3 600 43.1 43.2 0.2 650 60.4 60.6 0.3 750 92.3 92.4 0.3 注：规定喷口喉道直径为485 mm时，其对应角度为0°。
下载: 导出CSV
-
[1] 聂恰耶夫. 航空动力装置控制规律与特性[M]. 单凤桐,译. 北京: 国防工业出版社,1998. [2] 李伟,李军,董顺义. 喷管面积调节精度对某型涡扇发动机加力性能影响的数值仿真[J]. 航空动力学报,2005,20(4): 556-560. LI Wei,LI Jun,DONG Shunyi. Numerical simulation of the influence of nozzle area control accuracy on turbofan afterburning performance[J]. Journal of Aerospace Power,2005,20(4): 556-560. (in Chinese doi: 10.3969/j.issn.1000-8055.2005.04.006LI Wei, LI Jun, DONG Shunyi. Numerical simulation of the influence of nozzle area control accuracy on turbofan afterburning performance[J]. Journal of Aerospace Power, 2005, 20(4): 556-560. (in Chinese) doi: 10.3969/j.issn.1000-8055.2005.04.006 [3] 郝晓乐,申世才,高莎莎. 喷口前馈线对航空发动机加力接通结果的影响[J]. 燃气涡轮试验与研究,2017,30(3): 6-10. HAO Xiaole,SHEN Shicai,GAO Shasha. Investigation on the impact of control laws of feedback exhaust nozzle area to reheat lit results[J]. Gas Turbine Experiment and Research,2017,30(3): 6-10. (in ChineseHAO Xiaole, SHEN Shicai, GAO Shasha. Investigation on the impact of control laws of feedback exhaust nozzle area to reheat lit results[J]. Gas Turbine Experiment and Research, 2017, 30(3): 6-10. (in Chinese) [4] 李杰,李娜,张立伟,等. 一种发动机喷口面积控制系统仿真研究方法[J]. 计算机仿真,2014,31(6): 111-114,206. LI Jie,LI Na,ZHANG Liwei,et al. A simulation method for engine nozzle area control system[J]. Computer Simulation,2014,31(6): 111-114,206. (in ChineseLI Jie, LI Na, ZHANG Liwei, et al. A simulation method for engine nozzle area control system[J]. Computer Simulation, 2014, 31(6): 111-114, 206. (in Chinese) [5] 王松,高亚辉,王振华,等. 航空发动机喷口分油活门位移传感器容错控制研究[J]. 测控技术,2020,39(4): 97-100. WANG Song,GAO Yahui,WANG Zhenhua,et al. Fault tolerant control of aeroengine nozzle oil separator valve sensor[J]. Measurement & Control Technology,2020,39(4): 97-100. (in ChineseWANG Song, GAO Yahui, WANG Zhenhua, et al. Fault tolerant control of aeroengine nozzle oil separator valve sensor[J]. Measurement & Control Technology, 2020, 39(4): 97-100. (in Chinese) [6] 王向阳,朱纪洪,刘凯,等. 三轴承推力矢量喷管运动学建模及试验[J]. 航空学报,2014,35(4): 911-920. WANG Xiangyang,ZHU Jihong,LIU Kai,et al. Kinematic modeling and testing of 3-bearing swivel duct nozzle[J]. Acta Aeronautica et Astronautica Sinica,2014,35(4): 911-920. (in ChineseWANG Xiangyang, ZHU Jihong, LIU Kai, et al. Kinematic modeling and testing of 3-bearing swivel duct nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(4): 911-920. (in Chinese) [7] 崔昊. 无人机尾喷口作动系统控制技术研究[D]. 西安: 西北工业大学,2007. CUI Hao. Research on control technology of UAV tail nozzle actuating system[D]. Xi’an: Northwestern Polytechnical University,2007. (in ChineseCUI Hao. Research on control technology of UAV tail nozzle actuating system[D]. Xi’an: Northwestern Polytechnical University, 2007. (in Chinese) [8] 于华锋,郭迎清,郭佳伟,等. 某型涡扇发动机喷口控制系统数控改造方案设计[J]. 航空发动机,2020,46(1): 1-5. YU Huafeng,GUO Yingqing,GUO Jiawei,et al. Design of digital control transformation scheme for nozzle control system of a turbofan engine[J]. Aeroengine,2020,46(1): 1-5. (in ChineseYU Huafeng, GUO Yingqing, GUO Jiawei, et al. Design of digital control transformation scheme for nozzle control system of a turbofan engine[J]. Aeroengine, 2020, 46(1): 1-5. (in Chinese) [9] 孔迪,曲山. 航空发动机矢量喷管控制系统试验研究[J]. 航空发动机,2014,40(6): 52-57. KONG Di,QU Shan. Experimental study on aeroengine vectoring nozzle control system[J]. Aeroengine,2014,40(6): 52-57. (in ChineseKONG Di, QU Shan. Experimental study on aeroengine vectoring nozzle control system[J]. Aeroengine, 2014, 40(6): 52-57. (in Chinese) [10] 王春民,沙超,魏学峰,等. 基于AMESim和Ansoft的直动式电磁阀动态特性仿真分析[J]. 机床与液压,2017,45(21): 160-163,148. WANG Chunmin,SHA Chao,WEI Xuefeng,et al. Simulation analysis of dynamic characteristics of direct-acting solenoid valve based on AMESim and Ansoft[J]. Machine Tool & Hydraulics,2017,45(21): 160-163,148. (in Chinese doi: 10.3969/j.issn.1001-3881.2017.21.037WANG Chunmin, SHA Chao, WEI Xuefeng, et al. Simulation analysis of dynamic characteristics of direct-acting solenoid valve based on AMESim and Ansoft[J]. Machine Tool & Hydraulics, 2017, 45(21): 160-163, 148. (in Chinese) doi: 10.3969/j.issn.1001-3881.2017.21.037 [11] 张义,周权,陈鹏飞,等. 基于机器视觉的航空发动机喷口喉道截面直径自动标定技术研究[J]. 智能机器人,2017(3): 54-57. ZHANG Yi,ZHOU Quan,CHEN Pengfei,et al. Automatic calibration technology of aero-engine nozzle throat section area based on machine perspective[J]. Intelligent Robot,2017(3): 54-57. (in ChineseZHANG Yi, ZHOU Quan, CHEN Pengfei, et al. Automatic calibration technology of aero-engine nozzle throat section area based on machine perspective[J]. Intelligent Robot, 2017(3): 54-57. (in Chinese) [12] 吴立巍. 基于图像分析的发动机尾喷口面积测量技术研究[J]. 信息与电脑,2016(14): 28-29. WU Liwei. Measurement technology study on engine tail nozzle area based on image analysis[J]. China Computer & Communication,2016(14): 28-29. (in Chinese doi: 10.3969/j.issn.1003-9767.2016.14.010WU Liwei. Measurement technology study on engine tail nozzle area based on image analysis[J]. China Computer & Communication, 2016(14): 28-29. (in Chinese) doi: 10.3969/j.issn.1003-9767.2016.14.010 [13] 史妍,张义,陈鹏飞,等. 基于改进方法的航空发动机喷口喉道截面直径测量技术研究[J]. 智能机器人,2019(3): 72-74. SHI Yan,ZHANG Yi,CHEN Pengfei,et al. Measurement technology study on aero-engine tail nozzle throat section diameter based on improved method[J]. Intelligent Robot,2019(3): 72-74. (in ChineseSHI Yan, ZHANG Yi, CHEN Pengfei, et al. Measurement technology study on aero-engine tail nozzle throat section diameter based on improved method[J]. Intelligent Robot, 2019(3): 72-74. (in Chinese) [14] 李杨,韦周庆,马寅月. 航空发动机异常收喷口故障分析[J]. 中国新技术新产品,2020(6): 61-62. LI Yang,WEI Zhouqing,MA Yinyue. Fault analysis of abnormal nozzle of aero-engine[J]. New Technology & New Products of China,2020(6): 61-62. (in ChineseLI Yang, WEI Zhouqing, MA Yinyue. Fault analysis of abnormal nozzle of aero-engine[J]. New Technology & New Products of China, 2020(6): 61-62. (in Chinese) [15] 周燕,王曦,姜晓峰,等. 航空发动机喷口收放异常故障诊断与分析[J]. 燃气涡轮试验与研究,2016,29(6): 34-37. ZHOU Yan,WANG Xi,JIANG Xiaofeng,et al. Diagnoses and analysis of the failure of an engine nozzle control[J]. Gas Turbine Experiment and Research,2016,29(6): 34-37. (in ChineseZHOU Yan, WANG Xi, JIANG Xiaofeng, et al. Diagnoses and analysis of the failure of an engine nozzle control[J]. Gas Turbine Experiment and Research, 2016, 29(6): 34-37. (in Chinese) [16] 张秀云,崔利丰,马端杰. 航空发动机喷口收放转速和α2角度同时突变故障分析[J]. 航空发动机,2014,40(5): 23-27. ZHANG Xiuyun,CUI Lifeng,MA Duanjie. Failure analysis on abrupt changing of engine speed at Min/max nozzle status and α2 angle of an aeroengine[J]. Aeroengine,2014,40(5): 23-27. (in ChineseZHANG Xiuyun, CUI Lifeng, MA Duanjie. Failure analysis on abrupt changing of engine speed at Min/max nozzle status and α2 angle of an aeroengine[J]. Aeroengine, 2014, 40(5): 23-27. (in Chinese) [17] 陈晓涛,骆润,南斌斌. 浅析某型发动机喷口加力调节器故障原因[J]. 航空维修与工程,2017(4): 86-87. CHEN Xiaotao,LUO Run,NAN Binbin. Fault analysis on nozzle after-burning regulator of engine[J]. Aviation Maintenance & Engineering,2017(4): 86-87. (in ChineseCHEN Xiaotao, LUO Run, NAN Binbin. Fault analysis on nozzle after-burning regulator of engine[J]. Aviation Maintenance & Engineering, 2017(4): 86-87. (in Chinese) [18] KALA Z. Sensitivity analysis of the stability problems of thin-walled structures[J]. Journal of Constructional Steel Research,2005,61(3): 415-422. doi: 10.1016/j.jcsr.2004.08.005 [19] 余鹏明,管孝艳,陈俊英,等. 基于Spearman秩相关的再生水利用量影响因素研究[J]. 节水灌溉,2019(10): 78-82,88. YU Pengming,GUAN Xiaoyan,CHEN Junying,et al. Study on factors affecting reclaimed water utilization based on spearman rank correlation[J]. Water Saving Irrigation,2019(10): 78-82,88. (in ChineseYU Pengming, GUAN Xiaoyan, CHEN Junying, et al. Study on factors affecting reclaimed water utilization based on spearman rank correlation[J]. Water Saving Irrigation, 2019(10): 78-82, 88. (in Chinese) [20] 安建川. 输气管道泄漏模型不确定性因素敏感性分析[J]. 西南石油大学学报(自然科学版),2021,43(1): 149-156. AN Jianchuan. Sensitivity analysis for uncertain factors of gas pipeline leakage model[J]. Journal of Southwest Petroleum University (Science & Technology Edition),2021,43(1): 149-156. (in ChineseAN Jianchuan. Sensitivity analysis for uncertain factors of gas pipeline leakage model[J]. Journal of Southwest Petroleum University (Science & Technology Edition), 2021, 43(1): 149-156. (in Chinese) [21] 任泽凯. 基于MATLAB和ADAMS的四连杆机构运动仿真[J]. 装备机械,2016(3): 55-58,65. REN Zekai. Motion simulation of four-bar linkage based on MATLAB and ADAMS[J]. The Magazine on Equipment Machinery,2016(3): 55-58,65. (in ChineseREN Zekai. Motion simulation of four-bar linkage based on MATLAB and ADAMS[J]. The Magazine on Equipment Machinery, 2016(3): 55-58, 65. (in Chinese) [22] 林成龙,马义中,肖甜丽,等. 基于PLS方法和Kriging模型的多目标有效全局优化方法及应用[J]. 系统工程理论与实践,2021,41(7): 1855-1867. LIN Chenglong,MA Yizhong,XIAO Tianli,et al. Multi-objective efficient global optimization method and its application based on PLS method and Kriging model[J]. Systems Engineering-Theory & Practice,2021,41(7): 1855-1867. (in ChineseLIN Chenglong, MA Yizhong, XIAO Tianli, et al. Multi-objective efficient global optimization method and its application based on PLS method and Kriging model[J]. Systems Engineering-Theory & Practice, 2021, 41(7): 1855-1867. (in Chinese) -
点击查看大图
计量
- 文章访问数: 566
- HTML浏览量: 232
- PDF量: 37
- 被引次数: 0