某型航空发动机涡轮转子叶片断裂分析

杨木金; 陆松兵; 杨大兵; 杨合理; 潘彭杰

doi:10.13224/j.cnki.jasp.20240062

某型航空发动机涡轮转子叶片断裂分析

doi: 10.13224/j.cnki.jasp.20240062

1.
国营长虹机械厂，广西桂林 541002
2.
清华大学航空发动机研究院，北京 100084
3.
广西虹鹰动力科技有限公司，广西桂林 541002

详细信息

作者简介:
杨木金（1996-），男，硕士，主要从事航空发动机结构分析工作。E-mail：yangmujing2019@163.com

通讯作者:
杨合理（1989-），男，博士，主要从事航空发动机总体工作。E-mail：yhl20@mails.tsinghua.edu.cn

中图分类号: V232.3；TH113.7；O327
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出版历程
- 收稿日期: 2024-01-26
- 网络出版日期: 2025-09-24

Fracture analysis of turbine rotor blades in an aircraft engine

1.
State-owned Changhong Machinery Factory，Guilin Guangxi 541002，China
2.
Instiute for Aero Engine，Tsinghua University，Beijing 100084，China
3.
Guangxi Hawk Power Technology Company Limited，Guilin Guangxi 541002，China

摘要

摘要:
针对某型航空发动机在试验过程中出现涡轮转子叶片断裂故障的情况，通过外观检查、荧光检测、能谱分析、强度分析、叶片振动分析等手段对故障涡轮转子进行了研究。研究发现：排除外物损伤、材质缺陷、铸造工艺缺陷等因素，经叶片断口检查确认了叶片断裂故障模式为疲劳失效；通过仿真分析手段，最终锁定了叶片疲劳失效的原因为离心载荷、热载荷作用所产生的静应力与经过燃烧室蒸发管的高频气流激励引起的振动应力共同叠加所致。提出减少燃烧室蒸发管数目，加厚涡轮转子叶片尾缘厚度的方案，降低了气流激励频率，使得全转速范围内叶片固有频率与激励频率无交点，避免了涡轮转子叶片因共振而导致疲劳故障。
- 涡轮转子叶片 /
- 断裂分析 /
- 仿真分析 /
- 气流激励 /
- 疲劳失效
Abstract:
In response to the occurrence of turbine rotor blade fracture failures during the testing process of an aeroengine, research on the failed turbine rotor was conducted through visual inspection, fluorescence detection, energy spectrum analysis, strength analysis, and blade vibration analysis. It was found that after eliminating factors such as foreign object damage, material defects, and casting process defects, the fracture failure mode of the blade was confirmed as fatigue failure through blade fracture inspection. Through simulation analysis, it was ultimately determined that the cause of blade fatigue failure was the combined effects of static stress generated by centrifugal load and thermal load, and vibration stress caused by high-frequency airflow excitation through the combustion chamber evaporation tube. A scheme was proposed to reduce the number of combustion chamber evaporation tubes and thicken the trailing edge of the turbine rotor blades, reducing the flow excitation frequency so that there was no intersection between the natural frequency of the blades and the excitation frequency within the full speed range, thus avoiding fatigue failure of the turbine rotor blades due to resonance.
- turbine rotor blade /
- fracture analysis /
- simulation analysis /
- airflow excitation /
- fatigue failure

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图 1 涡轮转子叶片故障模式

Figure 1. Turbine rotor blade failure mode

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图 2 涡轮转子故障情况

Figure 2. Fault situation of turbine rotor

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图 3 涡轮盘荧光检查

Figure 3. Fluoroscopy of turbine disk

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图 4 断裂叶片体视镜检查断口形貌

Figure 4. Visual inspection of fracture surface morphology of fractured blades using a stereo microscope

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图 5 扫描电镜检查结果

Figure 5. Scanning electron microscopy examination results

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图 6 温度场加载

Figure 6. Temperature field loading

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图 7 网格无关性验证

Figure 7. Grid independence verification

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图 8 涡轮叶片应力分布

Figure 8. Stress distribution of turbine blades

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图 9 转子系统的坎贝尔图

Figure 9. Campbell diagram of rotor system

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图 10 不同激励对应的坎贝尔图

Figure 10. Campbell diagram corresponding to different excitations

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图 11 第4阶模态的振动应力

Figure 11. Vibration stress of the fourth mode

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图 12 气流激励作用下叶片不同角度的应力分布

Figure 12. Stress distribution of blade at different angles under airflow excitation

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图 13 叶片Goodman图

Figure 13. Goodman diagram of blades

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图 14 优化设计后的坎贝尔图

Figure 14. Campbell diagram after optimized design

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表 1 能谱测试结果

Table 1. Energy spectrum test results %

元素	基体	K418
Al	7.21	5.50～6.40
Ti	0.95	0.50～1.00
Cr	13.12	11.50～13.50
Ni	69.71	余
Mo	4.60	3.40～3.80
Nb	2.41	1.80～2.50
Mn	1.21	<0.50

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表 2 涡轮转子叶片的几何参数

Table 2. Geometric parameters of turbine rotor blades mm

参数	转子叶片
叶高	27.70
平均轴向弦长	12.60
前缘半径	0.80
尾缘半径	0.30

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表 3 涡轮材料参数

Table 3. Material parameters of the turbine

温度/ ℃	热导率/ （W/（m·℃））	线膨胀系数/ （10⁻⁶/℃）	弹性模量 E/GPa	泊松比 μ
100	10.15	12.60	205	0.25
200	11.72	12.70	200	0.25
300	12.98	12.90	195	0.25
400	14.65	13.40	190	0.25
500	16.33	13.70	184	0.25
600	18.42	14.20	179	0.25
700	20.52	14.70	171	0.25
800	22.61	15.50	165	0.26
900	24.28	15.50	156	0.26

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表 4 弯曲模态对应的临界转速

Table 4. Critical speed corresponding to the bending %

模态	相对临界转速
1阶，反进动	28.15
1阶，正进动	34.63
2阶，反进动	43.60
2阶，正进动	59.44

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表 5 激励源和数量

Table 5. Excitation sources and quantity

激励源	数目
蒸发管	18
导向器叶片	36
尾喷管支架	6

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参考文献(20)

[1]	CARTA M, GHISU T, SHAHPAR S. Heat transfer analysis of damaged shrouded high-pressure turbine rotor blades[J]. International Journal of Turbomachinery, Propulsion and Power, 2023, 8(3): 1-12.
[2]	CARTER T J. Common failures in gas turbine blades[J]. Engineering Failure Analysis, 2005, 12(2): 237-247. doi: 10.1016/j.engfailanal.2004.07.004
[3]	陈懋章, 刘宝杰. 风扇/压气机气动设计技术发展趋势: 用于大型客机的大涵道比涡扇发动机[J]. 航空动力学报, 2008, 23(6): 961-975. CHEN Maozhang, LIU Baojie. Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan[J]. Journal of Aerospace Power, 2008, 23(6): 961-975. (in Chinese CHEN Maozhang, LIU Baojie. Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan[J]. Journal of Aerospace Power, 2008, 23(6): 961-975. (in Chinese)
[4]	丁水汀, 褚军涛, 李果. 基于主动热载荷管理技术的涡轮盘疲劳寿命[J]. 航空动力学报, 2018, 33(8): 1896-1904. DING Shuiting, CHU Juntao, LI Guo. Fatigue life of turbine disk based on actively managed thermal loading method[J]. Journal of Aerospace Power, 2018, 33(8): 1896-1904. (in Chinese DING Shuiting, CHU Juntao, LI Guo. Fatigue life of turbine disk based on actively managed thermal loading method[J]. Journal of Aerospace Power, 2018, 33(8): 1896-1904. (in Chinese)
[5]	陶春虎, 钟培道, 王仁智, 等. 航空发动机转动部件的失效与预防[M]. 北京: 国防工业出版社, 2000. TAO Chunhu, ZHONG Peidao, WANG Renzhi, et al. Failure analysis and prevention for rotor in aero-engine[M]. Beijing: National Defense Industry Press, 2000. (in Chinese TAO Chunhu, ZHONG Peidao, WANG Renzhi, et al. Failure analysis and prevention for rotor in aero-engine[M]. Beijing: National Defense Industry Press, 2000. (in Chinese)
[6]	荆甫雷, 王荣桥, 胡殿印. 一种单晶涡轮叶片热机械疲劳寿命评估方法[J]. 航空动力学报, 2016, 31(2): 299-306. JING Fulei, WANG Rongqiao, HU Dianyin. A thermo-mechanical fatigue life assessment method for single crystal turbine blades[J]. Journal of Aerospace Power, 2016, 31(2): 299-306. (in Chinese JING Fulei, WANG Rongqiao, HU Dianyin. A thermo-mechanical fatigue life assessment method for single crystal turbine blades[J]. Journal of Aerospace Power, 2016, 31(2): 299-306. (in Chinese)
[7]	ZHANG Ming, LIU Yan, WANG Weiqiang, et al. The fatigue of impellers and blades[J]. Engineering Failure Analysis, 2016, 62: 208-231. doi: 10.1016/j.engfailanal.2016.02.001
[8]	HEUER T, GUGAU M, KLEIN A, et al. An analytical approach to support high cycle fatigue validation for turbocharger turbine stages[C]// Turbo expo: power for Land, Sea, and Air. Berlin, Germany: ASME, 2008: 723-732.
[9]	MISHRA R K, THOMAS J, SRINIVASAN K, et al. Fatigue failure of LP compressor blade in an aero gas turbine engine[J]. Journal of Failure Analysis and Prevention, 2014, 14(3): 296-302. doi: 10.1007/s11668-014-9808-4
[10]	洪杰, 刘书国, 张大义, 等. 小型短寿命涡扇发动机涡轮叶片疲劳失效分析[J]. 航空动力学报, 2012, 27(3): 604-609. HONG Jie, LIU Shuguo, ZHANG Dayi, et al. Fatigue failure analysis of turbine blade in miniature short-life turbofan engine[J]. Journal of Aerospace Power, 2012, 27(3): 604-609. (in Chinese HONG Jie, LIU Shuguo, ZHANG Dayi, et al. Fatigue failure analysis of turbine blade in miniature short-life turbofan engine[J]. Journal of Aerospace Power, 2012, 27(3): 604-609. (in Chinese)
[11]	SHIBUKAWA N, TEJIMA T, IWASAKI Y, et al. A correlation between vibration stresses and flow features of steam turbine long blades in low load conditions[C]// ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. Vancouver, Canada: ASME, 2011: 2437-2446.
[12]	LIU Yixiong, YANG Ce, MA Chaochen, et al. Forced responses on a radial turbine with nozzle guide vanes[J]. Journal of Thermal Science, 2014, 23(2): 138-144. doi: 10.1007/s11630-014-0688-4
[13]	周金满, 薛强, 杨硕, 等. 外物损伤对压气机叶片高周疲劳强度的影响研究进展[J]. 航空发动机, 2023, 49(1): 27-33. ZHOU Jinman, XUE Qiang, YANG Shuo, et al. A systematic review on effect of FOD on HCF strength of compressor blades[J]. Aeroengine, 2023, 49(1): 27-33. (in Chinese ZHOU Jinman, XUE Qiang, YANG Shuo, et al. A systematic review on effect of FOD on HCF strength of compressor blades[J]. Aeroengine, 2023, 49(1): 27-33. (in Chinese)
[14]	许祥胜, 赵振华, 陈伟. 外物损伤对TC4钛合金的高周疲劳强度的影响[J]. 航空发动机, 2017, 43(3): 88-92. XU Xiangsheng, ZHAO Zhenhua, CHEN Wei. The influences of foreign object damage on the high cycle fatigue behavior of titanium alloy TC4[J]. Aeroengine, 2017, 43(3): 88-92. (in Chinese XU Xiangsheng, ZHAO Zhenhua, CHEN Wei. The influences of foreign object damage on the high cycle fatigue behavior of titanium alloy TC4[J]. Aeroengine, 2017, 43(3): 88-92. (in Chinese)
[15]	薛志博, 杨金侠, 由宝财. 动力涡轮工作叶片与导向叶片振动疲劳性能差异分析[J]. 航空发动机, 2020, 46(6): 41-45. XUE Zhibo, YANG Jinxia, YOU Baocai. Analysis on difference of vibration fatigue properties between blade and vane of power turbine[J]. Aeroengine, 2020, 46(6): 41-45. (in Chinese XUE Zhibo, YANG Jinxia, YOU Baocai. Analysis on difference of vibration fatigue properties between blade and vane of power turbine[J]. Aeroengine, 2020, 46(6): 41-45. (in Chinese)
[16]	王辉. R20燃气轮机涡轮工作叶片断裂失效分析[J]. 燃气轮机技术, 2023, 36(2): 62-67, 72. WANG Hui. Failure analysis of turbine blade fracture in R20 gas turbine[J]. Gas Turbine Technology, 2023, 36(2): 62-67, 72. (in Chinese WANG Hui. Failure analysis of turbine blade fracture in R20 gas turbine[J]. Gas Turbine Technology, 2023, 36(2): 62-67, 72. (in Chinese)
[17]	卜嘉利, 高志坤, 牛建坤, 等. 航空发动机风扇静子叶片裂纹失效分析[J]. 航空发动机, 2021, 47(6): 91-95. BU Jiali, GAO Zhikun, NIU Jiankun, et al. Crack failure analysis of a fan stator vane[J]. Aeroengine, 2021, 47(6): 91-95. (in Chinese BU Jiali, GAO Zhikun, NIU Jiankun, et al. Crack failure analysis of a fan stator vane[J]. Aeroengine, 2021, 47(6): 91-95. (in Chinese)
[18]	高志坤, 张成龙, 王威, 等. 重型燃气轮机压气机第一级转子叶片断裂分析[J]. 航空发动机, 2021, 47(1): 47-52. GAO Zhikun, ZHANG Chenglong, WANG Wei, et al. Fracture analysis of first stage rotor blade of heavy gas turbine compressor[J]. Aeroengine, 2021, 47(1): 47-52. (in Chinese GAO Zhikun, ZHANG Chenglong, WANG Wei, et al. Fracture analysis of first stage rotor blade of heavy gas turbine compressor[J]. Aeroengine, 2021, 47(1): 47-52. (in Chinese)
[19]	田少杰, 漆文凯, 许正华. 气流激励下叶片振动响应分析方法[J]. 航空动力学报, 2021, 36(4): 826-838. TIAN Shaojie, QI Wenkai, XU Zhenghua. Method of blade vibration response analysis under airflow excitation[J]. Journal of Aerospace Power, 2021, 36(4): 826-838. (in Chinese TIAN Shaojie, QI Wenkai, XU Zhenghua. Method of blade vibration response analysis under airflow excitation[J]. Journal of Aerospace Power, 2021, 36(4): 826-838. (in Chinese)
[20]	赵虹桥. 涡轮高周疲劳失效分析及寿命-可靠性评估方法研究[D]. 北京: 北京理工大学, 2018. ZHAO Hongqiao. Study on high cycle fatigue failure analysis and life-reliability evaluation method of turbine[D]. Beijing: Beijing Institute of Technology, 2018. (in Chinese ZHAO Hongqiao. Study on high cycle fatigue failure analysis and life-reliability evaluation method of turbine[D]. Beijing: Beijing Institute of Technology, 2018. (in Chinese)