周向进气畸变对篦齿封严环气弹稳定性影响研究

摘要
图/表
参考文献(23)
相关文章 (15)

全文: PDF (3988 KB) HTML (1 KB)
输出: BibTeX | EndNote (RIS)

摘要针对航空发动机篦齿封严环在周向进气畸变状态下的气弹稳定性问题，采用三维插值和非定常动网格技术，建立了基于能量法的篦齿封严环气弹稳定性求解模型，在验证求解模型准确性的基础上，研究了对称进气与非对称进气、进气畸变程度对篦齿封严环气弹稳定性的影响规律，分析了气动功在齿腔不同区域分布特性，揭示了周向进气畸变对篦齿封严环气弹稳定性影响机理。研究表明，周向进气畸变可改变气动阻尼比，对篦齿封严环气弹稳定性影响较大。非对称进气时，篦齿封严环气弹稳定性随畸变度的增加先降低后增加再降低。对称进气时，篦齿封严环气弹稳定性随畸变度的增加先增加后降低，相对于非对称进气畸变，对称进气方式对气弹稳定状态影响较小。篦齿封严环在发生气弹失稳时，周向进气畸变对气动功影响最大的区域位于首级篦齿迎风区域，是流场周向压力均匀性最差的区域，周向进气畸变的影响随相对距离增加而降低；篦齿封严环所有齿腔底部的总气动功受周向进气畸变影响较大，在进行结构设计时可改变齿腔底部尺寸、形状等，以降低周向进气畸变对篦齿封严环气弹稳定性的影响。

	服务

	把本文推荐给朋友
	加入我的书架
	加入引用管理器
	E-mail Alert
	RSS
	作者相关文章
	苏国征1
	2
	孙丹1
	2
	王志1
	2
	李玉1
	2
	王文3
	徐梅鹏3

关键词 ：篦齿封严环, 气弹稳定性, 周向进气畸变, 气动阻尼比, 能量法

Abstract：Aiming at the aeroelastic stability of the labyrinth seal ring of aero-engine under circumferential intake distortion, a solution model for the aeroelastic stability of the labyrinth seal ring based on the energy method was established by using three-dimensional interpolation and unsteady dynamic grid technology. On the basis of verifying the accuracy of the solution model, the influence law of symmetric intake distortion, asymmetric intake distortion and intake distortion degree on the aeroelastic stability of the labyrinth seal ring was studied, and the distribution characteristics of aerodynamic work in different regions of the tooth cavity were analyzed. The influence mechanism of circumferential intake distortion on the aeroelastic stability of labyrinth seal ring was revealed. The results show that the circumferential intake distortion can change the aerodynamic damping ratio and has a great influence on the aeroelastic stability of the labyrinth seal ring. In the case of asymmetric intake, the aeroelastic stability of labyrinth seal ring decreases first, then increases and then decreases with the increase of distortion degree. For symmetric intake, the aeroelastic stability of labyrinth seal ring first increases and then decreases with the increase of distortion degree. Compared with the asymmetric intake distortion, the aeroelastic stability of labyrinth seal ring is less affected. In the case of aeroelastic instability, the region with the greatest influence of circumferential intake distortion on aerodynamic work of the labyrinth seal ring of the first tooth is located in the windward region of the first labyrinth seal. It is the region with the worst circumferential pressure uniformity of the flow field. The influence of circumferential intake distortion decreases with the increase of relative distance. The total aerodynamic work at the bottom of the labyrinth seal ring is greatly affected by circumferential air intake distortion. The size and shape of the bottom cavity can be changed during the structural design to reduce the influence of circumferential air intake distortion on the aeroelastic stability of the labyrinth seal ring.

Key words： labyrinth seal ring aeroelastic stability circumferential intake distortion aerodynamic damping ratio energy method

收稿日期: 2023-05-04 出版日期: 2024-04-15

引用本文:

苏国征1,2，孙丹1,2，王志1,2，李玉1,2，王文3，徐梅鹏3. 周向进气畸变对篦齿封严环气弹稳定性影响研究[J]. 振动与冲击, 2024, 43(7): 57-66.
SU Guozheng1,2, SUN Dan1,2, WANG Zhi1,2, LI Yu1,2, WANG Wen3, XU Meipeng3. Effects of circumferential intake distortion on aeroelastic stability of labyrinth seal ring. JOURNAL OF VIBRATION AND SHOCK, 2024, 43(7): 57-66.

链接本文:

http://jvs.sjtu.edu.cn/CN/ 或 http://jvs.sjtu.edu.cn/CN/Y2024/V43/I7/57

[1] 孔晓治, 刘高文, 雷昭, 等. 齿型对压气机级间封严特性影响的实验研究[J]. 推进技术, 2018, 39(9): 2085-2093. KONG Xiaozhi, LIU Gaowen, LEI Zhao, et al. Experimental investigation for effects of tooth shapes on compressor inter-stage seal[J]. Journal of Propulsion Technology, 2018, 39(9): 2085-2093. [2] 王佳蓉, 张万福, 姜广政, 等.逆滞流迷宫密封气流激振特性研究[J]. 振动与冲击, 2021, 40(18): 33-41+62. WANG Jiarong, ZHANG Wanfu, JIANG Guangzheng, et al. Fluid-induced vibration characteristics of anti-stagnant labyrinth seals[J]. Journal of Vibration and Shock, 2021, 40(18): 33-41+62. [3] 宁喜, 王维民, 张娅, 等. 离心式压缩机密封动态特性分析及稳定性评价[J]. 振动与冲击, 2013, 32(13): 153-158. NING Xi, WANG Weimin, ZHANG Ya, et al. Dynamic performance analysis of seals in a centrifugal compressor and rotor stability evaluation[J]. Journal of Vibration and Shock, 2013, 32(13): 153-158. [4] 《航空发动机设计手册》总编委会. 航空发动机设计手册-第18册,叶片轮盘及主轴强度设计[M]. 北京: 航空工业出版社, 2001. [5] HARRY I, ROBERT J L. Inlet-air distortion effects on stall, surge, and acceleration margin of a turbojet engine equipped with variable compressor inlet guide vanes[R]. NACA. 1955. [6] ROQUE C, ALMUDENA V. Conceptual flutter analysis of labyrinth seals using analytical models. part I: theoretical support[C]// Turbomachinery technical conference and exposition, 2018. [7] ALMUDENA V, ROQUE C. Conceptual flutter analysis of labyrinth seals using analytical models. Part Ⅱ：physical interpretation[C]. Turbomachinery tech-nical conference and exposition, 2018. [8] PHIBEL R, MARE L D, GREEN J S, et al. Numerical investigation of labyrinth seal aeroelastic stability[C]// ASME turbo expo 2009: Power for land, sea, and air. 2009. [9] PHIBEL R. A numerical investigation of labyrinth seal flutter[D], London: University of London, 2012. [10] ZHUANG Q. Parametric study on the aeroelastic stability of rotor seals[D]. Turbomachinery Aeromechanical University Training, 2012. [11] WANG N M, WANG Y R. Aeroelastic stability of labyrinth seal with different structure parameters[C]// Matec web of conferences, 2018. [12] WANG N M, WANG Y R, TIAN A M. Influence of structure parameters on aeroelastic stability for labyrinth seal based on energy method[J]. Propulsion and Power Research, 2018, 7(4): 288-295. [13] TOSHIMASA M, NAOTO S. Numerical and experimental studies of labyrinth seal aeroelastic instability[J]. Journal of Engineering for Gas Turbines and Power, 2019, 141 (11): 1-9. [14] 郭瑞, 杨建刚. 部分进汽对密封间隙流体激振力影响的研究[J]. 汽轮机技术, 2010, 52(3): 188-190. GUO Rui, YANG Jiangang. Research on fluid-induced vibra-tion characteristics of the control stage with eccentric tip clearances under partial admission conditions[J]. Turbine Technology, 2010, 52(3): 188-190. [15] 高庆水, 张万福, 张楚, 等. 部分进汽下汽轮机不稳定振动及抑制方法[J]. 机械工程学报, 2014, 50(5): 108-114. GAO Qingshui, ZHANG Wanfu, ZHANG Chu, et al. Turbine unstable vibration and its reduction method under partial admission mode[J]. Journal of Mechanical Engineering, 2014, 50(5): 108-114. [16] 张尧, 张万福, 顾乾磊, 等. 部分进汽下调节级叶顶偏心激振特性研究[J]. 动力工程学报, 2019, 39(5): 353-359. ZHANG Yao, ZHANG Wanfu, GU Qianlei, et al. Research on fluid-induced vibration characteristics of the control stage with eccentric tip clearances under partial admission conditions[J]. Journal of Chinese Society of Power Engineering, 2019, 39(5): 353-359. [17] 王能茂, 王延荣, 田爱梅. 篦齿封严结构气弹稳定性数值分析[J]. 航空动力学报, 2018, 33(5): 1144-1150. WANG Nengmao, WANG Yanrong, TIAN Aimei. Numerical analysis for aeroelastic stability of labyrinth seals[J]. Journal of aerospace power, 2018, 33(5): 1144-1150. [18] 郑赟, 杨慧, 田晓. 振荡压气机叶栅叶片表面非定常响应以及气弹稳定性分析[J]. 振动与冲击, 2012, 31(3): 111-116. ZHENG Yun, YANG Hui, TIAN Xiao. Unsteady aerodynamic response and aeroelastic stability of oscillating compressor cascade[J]. Journal of Vibration and Shock, 2012, 31(3): 111-116. [19] John D. Anderson. 计算流体力学基础及其应用[M]. 吴颂平, 刘赵淼, 译. 机械工业出版社, 2007: 13-17. [20] STOCKER H L, COX D M. Aerodynamic performance of conventional and advanced design labyrinth seals with solid-smooth, abradable, and honeycomb lands[R]. NASA, CR-135307,1977. [21] 高海洋. 畸变条件下端区流动对压气机稳定性影响的机理研究[D]. 大连: 大连海事大学, 2014. [22] 刘一雄, 刘廷毅, 王德友, 等. 基于能量法和特征值法的颤振预测数值方法研究[J]. 航空发动机, 2014, 40(6): 43-46. LIU Yixiong, LIU Tingyi, WANG Deyou, et al. Numerical Study of Flutter Prediction Based on Energy Method and Eigenvalue Method. [23] 王宇, 于晓光, 罗忠, 等. 不同边界条件下高速旋转带篦齿薄壁短圆柱壳的行波共振特性研究[J]. 振动与冲击, 2018, 37(10): 20-26+56. WANG Yu, YU Xiaoguang, LUO Zhong, et al. Travelling wave resonance characteristics of a high-speed rotating thin short cylindrical shell with sealing teeth in various boundary conditions[J]. Journal of Vibration and Shock, 2018, 37(10): 20-26+56.