Structure design and vibration reduction analysis of a certain type of un-derplatform damper
-
摘要:
为了研究叶片缘板阻尼装置对某型发动机燃气涡轮叶片振动的动力响应的影响，基于整体-局部统一滑动模型理论建立摩擦模型，结合有限元分析软件ANSYS和谐响应计算程序，对成组三齿涡轮叶片进行了仿真分析，当阻尼器和叶片缘板之间正压力与叶片受到的激振力比值在合适范围内，叶片第2阶共振幅值仿真结果可降至无阻尼状态下的25%以下，依据仿真分析结果，完成了两种涡轮叶片的缘板阻尼器结构设计。针对某型涡轮叶片高频振动模态，设计高频减振特性试验方案，搭建高频减振特性试验系统，开展成组涡轮叶片高阶模态减振试验，叶片第1阶共振幅值相对无阻尼状态可降至70.72%。结合仿真计算结果和实际试验结果，得到涡轮叶片减振特性影响参数，形成了一套针对危险模态下涡轮叶片缘板阻尼器的结构设计和试验验证方法。
Abstract:To investigate the impact of blade platform damping devices on the dynamic response of vibration in a certain type of aero-engine gas turbine blades, a friction model was established based on the global-local unified slip model theory. By integrating the finite element analysis software ANSYS and harmonic response calculation procedures, simulation analysis was conducted on grouped three-tooth turbine blades. When the ratio of the normal pressure between the damper and the blade platform to the excitation force acting on the blade fell within an appropriate range, the simulated resonance amplitude of the second-order mode of the blade can be reduced to below 25% of the undamped state. Based on the simulation results, structural designs for two types of turbine blade platform dampers were completed. For high-frequency vibration modes of a certain turbine blade, a high-frequency vibration reduction test plan was designed, and a corresponding test system was constructed. High-order modal vibration reduction tests were carried out on grouped turbine blades, and the first-order resonance amplitude was reduced to 70.72% of the undamped state. By combining simulation results with experimental data, key parameters influencing the vibration reduction characteristics of turbine blades were identified, leading to the development of a comprehensive methodology for the structural design and experimental validation of turbine blade platform dampers under critical modal conditions.
-
图 1 整体-局部统一滑动模型的力-位移迟滞回线
Figure 1. Force-displacement hysteresis loop of global-local unified sliding model
图 2 带摩擦阻尼装置叶片振动响应计算流程图
Figure 2. Flow chart of vibration response calculation of blade with friction damping device
图 4 不同正压力下涡轮叶片组幅频特性曲线
Figure 4. Amplitude-frequency characteristics of turbine blades under different positive pressures
图 5 涡轮叶片相对共振幅值随无量纲正压力的变化曲线
Figure 5. Curve of relative common amplitude of turbine blade with dimensionless positive pressure
图 7 三齿涡轮叶片阻尼装置结构及安装示意图
Figure 7. Structure and installation diagram of three-tooth turbine blade damping device
图 8 阻尼器在工作状态下等效应力云图
Figure 8. Equivalent stress diagram of the damper in working condition
图 9 涡轮叶片摩擦阻尼高频减振试验系统
Figure 9. High frequency vibration damping test system for turbine blade friction damping
图 12 三齿涡轮叶片第2阶加速度幅频曲线
Figure 12. Amplitude-frequency curve of the second order acceleration of a three-tooth turbine blade
图 14 不同正压力下三齿涡轮叶片第1阶模态减振试验幅频曲线
Figure 14. Amplitude-frequency curves of the first mode vibration attenuation test of three-tooth turbine blades under different positive pressure
图 15 相对共振幅值随无量纲正压力变化曲线
Figure 15. Relative common amplitude with dimensionless positive pressure
表 1 DZ125材料属性
Table 1. Material properties of DZ125
参数 数值 密度/（kg/m3） 8570 弹性模量/1011 Pa Ex 1.765 Ey 1.765 Ez 1.27 切变模量/1010 Pa Gxy 7 Gyz 1.07 Gxz 1.07 泊松比 Uxy 0.26 Uyz 0.49 Uxz 0.49 
下载: 导出CSV
表 2 涡轮叶片前4阶固有频率计算结果
Table 2. Calculation results of the first four natural frequencies of turbine blades
阶次 固有频率/Hz 第1阶 7942 第2阶 13012 第3阶 17716 第4阶 23891
下载: 导出CSV
表 3 三齿涡轮叶片自由模态试验数据与仿真数据对比
Table 3. Comparison of modal test data and simulation data of three-tooth turbine blades
参数 仿真数据 试验数据 相对误差/% 第1阶固有频率/Hz 12753 12080 −5.28
下载: 导出CSV
表 4 三齿涡轮叶片试验数据对比
Table 4. Comparison of test data of three-tooth turbine blades
阶次 频率/Hz 相对
误差/%模态试验 减振特性试验 第1阶 5700 5720 0.35 第2阶 12300 13070 6.26 第3阶 17500 17310 1.09
下载: 导出CSV
表 5 三齿涡轮叶片第1阶减振试验中不同正压力下加速度共振幅值及共振频率变化
Table 5. Changes of acceleration co-amplitude and resonance frequency under different positive pressure in the first order vibration reduction test of three-tooth turbine blades
正压力/N a/g 共振频率/Hz 相对共振幅值 0 77.16 5600 1 5 65.04 0.8429 10 59.99 0.7775 20 63.07 0.8174 40 55.03 0.7132 60 54.57 0.7072 100 68.95 0.8936
下载: 导出CSV
-
[1] 徐强. 准周期激励下带干摩擦阻尼叶片减振特性研究[D]. 南京: 南京航空航天大学, 2016. XU Qiang. Study on vibration reduction characteristics of blades with dry friction damping under quasi-periodic excitation[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in ChineseXU Qiang. Study on vibration reduction characteristics of blades with dry friction damping under quasi-periodic excitation[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese) [2] HARTOG J P D. Forced vibrations with combined coulomb and viscous friction[J]. Journal of Fluids Engineering, 1931, 53(2): 107-115. [3] IWAN W D. The dynamic response of bilinear hysteretic systems [D]. Pasadena, US: California Institute of Technology, 1961. [4] MENQ C H, BIELAK J, GRIFFIN J H. The influence of microslip on vibratory response: Part Ⅰ a new microslip model[J]. Journal of Sound and Vibration, 1986, 107(2): 279-293. doi: 10.1016/0022-460X(86)90238-5 [5] 漆文凯, 高德平. 摩擦阻尼减振设计中的局部滑动问题[J]. 航空学报, 2006, 27(5): 805-809. QI Wenkai, GAO Deping. Microslip study on friction damping and its application in design of vibration reduction[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(5): 805-809. (in ChineseQI Wenkai, GAO Deping. Microslip study on friction damping and its application in design of vibration reduction[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(5): 805-809. (in Chinese) [6] 漆文凯. 涡轮转子叶片叶根阻尼装置减振特性分析及实验研究[D]. 南京: 南京航空航天大学, 2005. QI Wenkai. Analysis and experimental study on damping characteristics of turbine rotor blade root damping device[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005. (in ChineseQI Wenkai. Analysis and experimental study on damping characteristics of turbine rotor blade root damping device[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005. (in Chinese) [7] GASTALDI C, GOLA M M. On the relevance of a microslip contact model for under-platform dampers[J]. International Journal of Mechanical Sciences, 2016, 115: 145-156. [8] ZUCCA S, BERRUTI T, COSI L. Experimental and numerical investigations on the dynamic response of turbine blades with tip pin dampers[J]. Journal of Physics: Conference Series, 2016, 744: 012131. doi: 10.1088/1742-6596/744/1/012131 [9] KRACK M, SALLES L, THOUVEREZ F. Vibration prediction of bladed disks coupled by friction joints[J]. Archives of Computational Methods in Engineering, 2017, 24(3): 589-636. doi: 10.1007/s11831-016-9183-2 [10] 李琳, 刘久周, 李超. 航空发动机中的干摩擦阻尼器及其设计技术研究进展[J]. 航空动力学报, 2016, 31(10): 2305-2317. LI Lin, LIU Jiuzhou, LI Chao. Research progress of dry friction dampers in aero engines and their design technology[J]. Journal of Aerospace Power, 2016, 31(10): 2305-2317. (in ChineseLI Lin, LIU Jiuzhou, LI Chao. Research progress of dry friction dampers in aero engines and their design technology[J]. Journal of Aerospace Power, 2016, 31(10): 2305-2317. (in Chinese) [11] 马艳红, 何龙江, 张大义, 等. 结构参数对带凸肩风扇静力学特性的影响分析[J]. 推进技术, 2015, 36(8): 1222-1228. MA Yanhong, HE Longjiang, ZHANG Dayi, et al. Investigation on effects of configuration parameters on static mechanical features for a shrouded fan[J]. Journal of Propulsion Technology, 2015, 36(8): 1222-1228. (in ChineseMA Yanhong, HE Longjiang, ZHANG Dayi, et al. Investigation on effects of configuration parameters on static mechanical features for a shrouded fan[J]. Journal of Propulsion Technology, 2015, 36(8): 1222-1228. (in Chinese) [12] ZUCCA S, DI MAIO D, EWINS D J. Measuring the performance of under platform dampers for turbine blades by rotating laser Doppler Vibrometer[J]. Mechanical Systems and Signal Processing, 2012, 32: 269-281. doi: 10.1016/j.ymssp.2012.05.011 [13] 李全通, 廖明夫, 陈卫, 等. 缘板干摩擦阻尼器叶片减振实验研究[J]. 机械科学与技术, 2008, 27(11): 1392-1396, 1400. LI Quantong, LIAO Mingfu, CHEN Wei, et al. An experimental study of decreasing vibration on blade with platform dry friction damper[J]. Mechanical Science and Technology for Aerospace Engineering, 2008, 27(11): 1392-1396, 1400. (in ChineseLI Quantong, LIAO Mingfu, CHEN Wei, et al. An experimental study of decreasing vibration on blade with platform dry friction damper[J]. Mechanical Science and Technology for Aerospace Engineering, 2008, 27(11): 1392-1396, 1400. (in Chinese) [14] 周显丁, 谢永慧, 吴君. 新型阻尼结构叶片振动特性试验研究[J]. 东方汽轮机, 2011(4): 4-10. ZHOU Xianding, XIE Yonghui, WU Jun. Experimental study on vibration characteristics of blades of new damping structures[J]. Dongfang Turbine, 2011(4): 4-10. (in ChineseZHOU Xianding, XIE Yonghui, WU Jun. Experimental study on vibration characteristics of blades of new damping structures[J]. Dongfang Turbine, 2011(4): 4-10. (in Chinese) [15] ZHANG Dayi, GAO Bin, HONG Jie, et al. Experimental investigation on dynamic response of flat blades with underplatform dampers[J]. Chinese Journal of Aeronautics, 2019, 32(12): 2667-2678. doi: 10.1016/j.cja.2019.04.022 [16] 陈茉莉, 李舜酩. 基于分布激励突卸的转子叶片阻尼比试验[J]. 航空动力学报, 2009, 24(11): 2521-2526. CHEN Moli, LI Shunming. Damping ratio experiment study on rotary blade based on distributing excitation unloaded instantaneously[J]. Journal of Aerospace Power, 2009, 24(11): 2521-2526. (in ChineseCHEN Moli, LI Shunming. Damping ratio experiment study on rotary blade based on distributing excitation unloaded instantaneously[J]. Journal of Aerospace Power, 2009, 24(11): 2521-2526. (in Chinese) [17] 何尚文, 张钦, 贾文祯, 等. 考虑正压力分配的B-B型涡轮叶片缘板阻尼器系统减振特性研究[J]. 河北科技大学学报, 2022, 43(4): 339-346. HE Shangwen, ZHANG Qin, JIA Wenzhen, et al. Study on vibration reduction characteristics of the B-B type turbine blade under-platform damper system considering the normal load allocation[J]. Journal of Hebei University of Science and Technology, 2022, 43(4): 339-346. (in ChineseHE Shangwen, ZHANG Qin, JIA Wenzhen, et al. Study on vibration reduction characteristics of the B-B type turbine blade under-platform damper system considering the normal load allocation[J]. Journal of Hebei University of Science and Technology, 2022, 43(4): 339-346. (in Chinese) [18] 李琳, 高钱, 吴亚光, 等. 考虑参数关联的缘板阻尼器减振性能分析[J]. 航空动力学报, 2021, 36(8): 1657-1668. LI Lin, GAO Qian, WU Yaguang, et al. Vibration damping performance analysis of edge plate damper considering parameter correlation[J]. Journal of Aerospace Power, 2021, 36(8): 1657-1668. (in ChineseLI Lin, GAO Qian, WU Yaguang, et al. Vibration damping performance analysis of edge plate damper considering parameter correlation[J]. Journal of Aerospace Power, 2021, 36(8): 1657-1668. (in Chinese) [19] 陈璐璐, 马艳红, 杨鑫, 等. 带干摩擦阻尼结构叶片振动响应试验[J]. 航空动力学报, 2008, 23(9): 1647-1653. CHEN Lulu, MA Yanhong, YANG Xin, et al. Experiment of vibration and response of blade with dry friction structure[J]. Journal of Aerospace Power, 2008, 23(9): 1647-1653. (in ChineseCHEN Lulu, MA Yanhong, YANG Xin, et al. Experiment of vibration and response of blade with dry friction structure[J]. Journal of Aerospace Power, 2008, 23(9): 1647-1653. (in Chinese) [20] 孙莹, 刘永泉, 郝燕平, 等. 带缘板摩擦阻尼片高压涡轮叶片的减振研究[J]. 航空发动机, 2014, 40(5): 57-61. SUN Ying, LIU Yongquan, HAO Yanping, et al. Vibration reduction of high pressure turbine blade with platform friction damper[J]. Aeroengine, 2014, 40(5): 57-61. (in ChineseSUN Ying, LIU Yongquan, HAO Yanping, et al. Vibration reduction of high pressure turbine blade with platform friction damper[J]. Aeroengine, 2014, 40(5): 57-61. (in Chinese) [21] 阳刚, 周标, 臧朝平, 等. 缘板阻尼结构减振特性的影响因素分析[J]. 航空动力学报, 2019, 34(1): 115-124. YANG Gang, ZHOU Biao, ZANG Chaoping, et al. Analysis of effect factors on damping characteristics for underplatform dampers[J]. Journal of Aerospace Power, 2019, 34(1): 115-124. (in ChineseYANG Gang, ZHOU Biao, ZANG Chaoping, et al. Analysis of effect factors on damping characteristics for underplatform dampers[J]. Journal of Aerospace Power, 2019, 34(1): 115-124. (in Chinese) -
点击查看大图
计量
- 文章访问数: 744
- HTML浏览量: 390
- PDF量: 41
- 被引次数: 0