Effect of variable camber guide vane on forced vibration of fan rotor blade
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摘要:
针对变弯度可调导叶尾迹激励引起的气动弹性问题，基于时间变换法和谐响应模态叠加法对一级半风扇转子进行强迫振动分析，研究了变弯度导叶不同弯角对风扇转子气动性能及其振动特性的影响。结果表明：随着导叶的打开，风扇转子流量增加，压比提高，效率增加，调节导叶对下游转子叶根部位影响更大。在气动激励方面，随着导叶的关闭，转子叶片表面气动力幅值增大，相位变化剧烈。导叶角度对所关注的高阶局部模态的气动阻尼影响较小，随着导叶的关闭，气动阻尼略有下降。总体上，当导叶角度偏离设计角度越大，下游转子叶片的振动响应越高，认为存在一个最优的导叶调节角度，使得转子叶片振动应力最小。
Abstract:In view of the aeroelastic problem caused by the wake excitation of variable camber guide vanes, forced vibration analysis of a 1.5 stage fan rotor was conducted with the utilization of the time transformation method and the harmonic response method. The effect of variable camber guide vane angle on the aerodynamic performance and vibration characteristics of the downstream rotor blade was studied. Results indicated that as the guide vane opened, the mass flow rate, pressure ratio, and efficiency all increased. Adjusting the guide vane had a greater impact on the root area of the rotor blade. For aerodynamic excitation, as the guide vane closed, the aerodynamic amplitude of the rotor blade increased and the phase changed sharply. The angle of the guide vane had little effect on the aerodynamic damping of the higher-order modes of concern. With the closing of guide vanes, the aerodynamic damping decreased slightly. Overall, the greater deviation of the guide vane angle from the design angle indicated the higher vibration response of the downstream rotor blade. It was considered that there was an optimal angle to minimize the vibration stress of the rotor blade.
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图 5 转子叶片第8阶振型和模态应力分布
Figure 5. 8th mode shape and modal stress distribution of rotor blade
图 6 进口导叶不同弯角的风扇转子模型
Figure 6. Fan rotor model with different angles of inlet guide vanes
图 8 不同网格密度下风扇转子压比-流量特性
Figure 8. Pressure ratio-mass flow characteristics of fan rotor under different mesh densities
图 10 设计角度下风扇转子的相对马赫数分布
Figure 10. Relative Mach number distribution of fan rotor at design angle
图 11 不同弯角下95%叶高的熵分布
Figure 11. Entropy distribution of 95% blade span under different angles
图 13 不同弯角下转子叶片表面流线图
Figure 13. Surface streamline of rotor blade under different angles
图 14 不同弯角下导叶气流转折角
Figure 14. Air flow turning angle of guide vanes under different angles
图 15 不同弯角下转子叶片进口气流角
Figure 15. Inlet airflow angle of rotor blade under different angles
图 16 不同弯角下转子叶片的导叶通过频率气动力幅值
Figure 16. Aerodynamic amplitude distribution of rotor blade at guide vane passing frequency under different angles
图 17 不同弯角下转子叶片的导叶通过频率气动力相位
Figure 17. Aerodynamic phase distribution of rotor blade at guide vane passing frequency under different angles
图 18 转子叶片90%叶高导叶通过频率下的压差幅值分布
Figure 18. Differential pressure amplitude of guide vane passing frequency at the 90% rotor blade span
图 19 转子叶片90%叶高导叶通过频率下的相位分布
Figure 19. Aerodynamic phase distribution of guide vane passing frequency at the 90% rotor blade span
图 21 不同弯角下转子叶片轴向振动幅值
Figure 21. Axial vibration amplitude of rotor blade under different angles
图 22 不同弯角下转子叶片周向正应力幅值
Figure 22. Circumferential normal stress of rotor blade under different angles
表 1 转子叶片几何参数
Table 1. Geometric parameters of rotor blade
名称 数值 前缘展长/叶尖弦长 1.57 叶尖前缘半径/叶尖弦长 2.49 叶尖前缘半径/叶尖弦长 2.44 进口轮毂比 0.37 出口轮毂比 0.50 叶片数量 22 
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表 2 不同弯角下风扇转子稳定裕度
Table 2. Stability margin of fan rotor under different angles
模型 M/% 导叶关闭5° 17.14 导叶关闭2.5° 14.50 设计角度 13.90 导叶打开2.5° 13.40 导叶打开5° 8.58
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表 3 不同弯角下转子叶片气动阻尼比
Table 3. Aerodynamic damping ratio of rotor blade under different angles
模型 气动阻尼比/% 导叶关闭5° 0.288 导叶关闭2.5° 0.295 设计角度 0.300 导叶打开2.5° 0.309 导叶打开5° 0.322
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表 4 不同弯角下转子叶片振动响应
Table 4. Vibration response of rotor blade under different angles
模型 Usum/mm σn/MPa 导叶关闭5° 0.142 28.71 导叶关闭2.5° 0.122 24.26 设计角度 0.055 12.87 导叶打开2.5° 0.153 32.27 导叶打开5° 0.168 35.44
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[1] JONES B A, OSCARSON R P. Single stage experimental evaluation of variable geometry guide vanes and stator blading [R]. NASA-CR-54588, 1968. [2] 熊劲松, 侯安平, 袁巍, 等. 可调叶片的发展趋势及其气动问题的探讨[J]. 航空动力学报, 2008, 23(1): 112-116. XIONG Jinsong, HOU Anping, YUAN Wei, et al. Some discuss on technology trend and aerodynamics problem of adjustable blade[J]. Journal of Aerospace Power, 2008, 23(1): 112-116. (in ChineseXIONG Jinsong, HOU Anping, YUAN Wei, et al. Some discuss on technology trend and aerodynamics problem of adjustable blade[J]. Journal of Aerospace Power, 2008, 23(1): 112-116. (in Chinese) [3] CROUSE J, STEINKE R J. Preliminary analysis of the effectiveness of variable-geometry guide vanes to control rotor-inlet flow conditions[R]. NASA-TN-D-3823, 1967. [4] LINDER C G, JONES B A. Single stage experimental evaluation of variable geometry guide vanes and stators[R]. NASA-CR-54555, 1967. [5] URASEK D C, STEINKE R J, CUNNAN W S. Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settings[R]. NASA-TN-D-8457, 1977. [6] RAJESH E, ROY B. Numerical study of variable camber inlet guide vane on low speed axial compressor[C]// Proceedings of the ASME 2015 Gas Turbine India Conference, Hyderabad, India: ASME, 2015: 1-12. [7] 刘占民, 赵凤声, 牟尚军, 等. 变弯度叶栅的试验研究[J]. 热能动力工程, 1991, 6(3): 113-121. LIU Zhanmin, ZHAO Fengsheng, MU Shangjun, et al. An experimental study of variable camber cascades[J]. Journal of Engineering for Thermal Energy and Power, 1991, 6(3): 113-121. (in ChineseLIU Zhanmin, ZHAO Fengsheng, MU Shangjun, et al. An experimental study of variable camber cascades[J]. Journal of Engineering for Thermal Energy and Power, 1991, 6(3): 113-121. (in Chinese) [8] 陆霄, 严明. 变弯度导叶对某1.5级压气机气动性能的影响[J]. 汽轮机技术, 2018, 60(6): 407-410, 460. LU Xiao, YAN Ming. Influence of variable inlet guide vane on a 1.5 stage compressor[J]. Turbine Technology, 2018, 60(6): 407-410, 460. (in ChineseLU Xiao, YAN Ming. Influence of variable inlet guide vane on a 1.5 stage compressor[J]. Turbine Technology, 2018, 60(6): 407-410, 460. (in Chinese) [9] 肖敏. 压气机可变弯度静子叶片特性的试验研究[J]. 燃气涡轮试验与研究, 2006, 19(2): 1-4. XIAO Min. Experimental investigation on the performance of variable curvature van of compressor stator[J]. Gas Turbine Experiment and Research, 2006, 19(2): 1-4. (in Chinese doi: 10.3969/j.issn.1672-2620.2006.02.001XIAO Min. Experimental investigation on the performance of variable curvature van of compressor stator[J]. Gas Turbine Experiment and Research, 2006, 19(2): 1-4. (in Chinese) doi: 10.3969/j.issn.1672-2620.2006.02.001 [10] 张国臣. 安装角异常和变弯度叶片对压气机性能影响机理的研究[D]. 西安: 西北工业大学, 2016. ZHANG Guochen. Study on the influence mechanism of abnormal installation angle and variable camber blades on compressor performance[D]. Xi’an: Northwestern Polytechnical University, 2016. (in ChineseZHANG Guochen. Study on the influence mechanism of abnormal installation angle and variable camber blades on compressor performance[D]. Xi’an: Northwestern Polytechnical University, 2016. (in Chinese) [11] 宫伟, 张宏武, 聂超群. 三级轴流压气机变工况条件下导叶/静叶和转速联动的调节规律[J]. 航空动力学报, 2009, 24(5): 1122-1128. GONG Wei, ZHANG Hongwu, NIE Chaoqun. Investigation on the aerodynamic adjustment between inlet guide-vane, stator, and operating speed of three-stage axial compressor[J]. Journal of Aerospace Power, 2009, 24(5): 1122-1128. (in ChineseGONG Wei, ZHANG Hongwu, NIE Chaoqun. Investigation on the aerodynamic adjustment between inlet guide-vane, stator, and operating speed of three-stage axial compressor[J]. Journal of Aerospace Power, 2009, 24(5): 1122-1128. (in Chinese) [12] ZHANG Xiaojie, WANG Yanrong, JIANG Xianghua. An efficient approach for predicting resonant response with the utilization of the time transformation method and the harmonic forced response method[J]. Aerospace, 2021, 8(11): 312. doi: 10.3390/aerospace8110312 [13] ZORI L, GALPIN P, CAMPREGHER R, et al. Time-transformation simulation of a 1.5 stage transonic compressor[J]. Journal of Turbomachinery, 2017, 139(7): 071001. doi: 10.1115/1.4035450 [14] CORNELIUS C, BIESINGER T, GALPIN P, et al. Experimental and computational analysis of a multistage axial compressor including stall prediction by steady and transient CFD methods[J]. Journal of Turbomachinery, 2014, 136(6): 061013. doi: 10.1115/1.4025583 [15] CONNELL S, HUTCHINSON B, GALPIN P, et al. The efficient computation of transient flow in turbine blade rows using transformation methods[C]// Proceedings of the ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, Copenhagen, Denmark: ASME, 2012: 2631-2640. [16] 李迪, 张晓杰, 王延荣. 压气机转子叶片的抑颤设计[J]. 推进技术, 2020, 41(9): 2120-2129. LI Di, ZHANG Xiaojie, WANG Yanrong. Design for flutter suppression of rotor blade in a compressor[J]. Journal of Propulsion Technology, 2020, 41(9): 2120-2129. (in ChineseLI Di, ZHANG Xiaojie, WANG Yanrong. Design for flutter suppression of rotor blade in a compressor[J]. Journal of Propulsion Technology, 2020, 41(9): 2120-2129. (in Chinese) [17] 付志忠. 叶轮机叶片流致振动数值预测方法研究[D]. 北京: 北京航空航天大学, 2016. FU Zhizhong. Numerical prediction method for flow-induced vibration of turbomachinery blades[D]. Beijing: Beihang University, 2016. (in ChineseFU Zhizhong. Numerical prediction method for flow-induced vibration of turbomachinery blades[D]. Beijing: Beihang University, 2016. (in Chinese) [18] MOFFATT S, HE L. Blade forced response prediction for industrial gas turbines: Part 1-methodologies[R]. ASME GT 2003-38640, 2003. [19] 胡骏. 航空叶片机原理[M]. 2版. 北京: 国防工业出版社, 2014. HU Jun. Principle of aviation blade machine[M]. 2nd ed. Beijing: National Defense Industry Press, 2014. (in ChineseHU Jun. Principle of aviation blade machine[M]. 2nd ed. Beijing: National Defense Industry Press, 2014. (in Chinese) [20] WILDHEIM S J. Excitation of rotationally periodic structures[J]. Journal of Applied Mechanics, 1979, 46(4): 878-882. doi: 10.1115/1.3424671 [21] OLSON B J, SHAW S W, SHI Chengzhi, et al. Circulant matrices and their application to vibration analysis[J]. Applied Mechanics Reviews, 2014, 66(4): 040803. doi: 10.1115/1.4027722 -
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