GH738高温合金涡轮机匣开裂原因
Cracking Cause of GH738 Superalloy Turbine Casing
摘 要
采用形貌观察、成分分析、组织观察、性能测试、热模拟试验等方法对某型航空发动机GH738高温合金涡轮机匣开裂的原因进行了分析，探讨了裂纹的性质及产生机理。结果表明：失效机匣中裂纹的性质为疲劳裂纹，裂纹源位于机匣前安装边挂钩外表面。机匣前安装边挂钩处的局部区域温度达到850~900℃，超过了GH738合金的允许使用温度（810℃），导致组织中γ'相体积分数降低，合金的力学性能和抗疲劳性能降低，从而促使了机匣过早疲劳开裂。
疲劳裂纹
超温
疲劳性能
turbine casing
fatigue crack
over-temperature
fatigue property
Abstract
The cause of cracking of GH738 super alloy turbine casing in an aeroengine was analyzed by morphology observation, component analysis, microstructure observation, performance testing and thermal simulation experiments, and the crack type and generating mechanism were discussed. The results show that the crack type in the failed casing was fatigue crack, and the crack source was located on the outer surface of the casing fixture fringe. The local temperature of the casing fixture fringe was 850-900 ℃, and exceeded the allowable service temperature (810 ℃) of GH738 alloy, which led to decrease of volume fraction of γ' phase in microstructure, and the mechanical properties and fatigue resistance of the alloy decreased, thereby promoted the premature fatigue cracking of the casing.
中图分类号 V252.2 DOI 10.11973/jxgccl202107017
所属栏目 失效分析
基金项目 航空动力基础研究项目
收稿日期 2020/5/13
修改稿日期 2021/2/24
网络出版日期
作者单位点击查看
备注李艳明(1990-),男,黑龙江绥化人,工程师,硕士
引用该论文: LI Yanming,MENG Lingqi,TONG Wenwei,LIU Huan. Cracking Cause of GH738 Superalloy Turbine Casing[J]. Materials for mechancial engineering, 2021, 45(7): 94～99
李艳明,孟令琪,佟文伟,刘欢. GH738高温合金涡轮机匣开裂原因[J]. 机械工程材料, 2021, 45(7): 94～99
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【2】傅依顺,沈毅,姜曦灼,等.某型航空发动机涡轮机匣选材论证分析[J].航空发动机,2011,37(6):45-48. FU Y S, SHEN Y, JIANG X Z, et al. Demonstration of material selection for an aeroengine turbine frame[J]. Aeroengine, 2011, 37(6):45-48.
【3】董建新.高温合金GH4738及应用[M].北京:冶金工业出版社,2014. DONG J X. Superalloy GH4738 and its application[M]. Beijing:Metallurgical Industry Press, 2014.
【4】TONG J, VERMEULEN B. The description of cyclic plasticity and visco plasticity of waspaloy using unified constitutive equations[J]. International Journal of Fatigue, 2003,25(5):413-420.
【5】姚志浩,董建新,张麦仓,等.GH738高温合金热加工行为[J].稀有金属材料与工程,2013,42(6):1199-1204. YAO Z H, DONG J X, ZHANG M C,et al. Hot deformation behaviour of superalloy GH738[J]. Rare Metal Materials and Engineering, 2013, 42(6):1199-1204.
【6】黄鹏跃,郭君伟.某型机高温合金材料机匣加工工艺研究[J].科技创新与应用,2015(16):132-132. HUANG P Y, GUO J W. Study on machining technology of superalloy casing for turbine[J]. Technology Innovation and Application, 2015(16):132-132.
【7】王琪,闫龙.非对称涡轮机匣的变形控制[J].中国新技术新产品,2014(18):13-13. WANG Q, YAN L. Deformation control of asymmetric turbine casing[J]. New Technologies and Products, 2014(18):13-13.
【8】魏志坚,徐文帅,袁慧,等.固溶温度对GH738合金环锻件组织性能的影响研究[J].模具工业,2017,43(9):63-67. WEI Z J, XU W S, YUAN H, et al. Effect of solution temperature on microstructure and mechanical properties of ring forgeable piece for GH738 alloy[J]. Die & Mould Industry, 2017, 43(9):63-67.
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【12】刘春风,张允华,张小勇,等.一种涡轮机匣挂钩槽疲劳寿命研究的试验方案[J].航空动力学报,2014,29(11):2735-2742. LIU C F, ZHANG Y H, ZHANG X Y, et al. An experimental scheme of investigating fatigue life of turbine casing slot[J]. Journal of Aerospace Power, 2014, 29(11):2735-2742.
【13】KURSUNA M, FUJITA S, SUGITA Y, et al. Thermal fatigue test for turbine housing by a pluses YAG laser[J]. Proceedings of the International Society for Optical Engineering, 2000, 3888:438-445.
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【17】姚志浩,董建新,张麦仓,等.固溶及稳定化工艺对GH738合金碳化物和γ'相析出规律的影响[J].材料热处理学报,2013,34(10):43-49. YAO Z H, DONG J X, ZHANG M C, et al. Influence of solution and stabilization heat treatment on carbide and gamma prime for super alloy GH738[J]. Transactions of Materials and Heat Treatment, 2013, 34(10):43-49.
【18】王珏,尚晓娟.多阶段热处理对GH738合金组织和室温硬度的影响[J].金属热处理,2015,40(12):97-102. WANG J, SHANG X J. Effect of multistage heat treatment on microstructure and room temperature hardness of GH738 alloy[J]. Heat Treatment of Metals, 2015, 40(12):97-102.
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