带涂层涡轮叶片载荷简化分析方法及载荷特性研究

刘林川; 侯成; 范学领; 周子扬

doi:10.21656/1000-0887.460201

带涂层涡轮叶片载荷简化分析方法及载荷特性研究

doi: 10.21656/1000-0887.460201

西安交通大学航天航空学院西安市极端环境服役性能与防护技术重点实验室，西安 710049

基金项目:

新材料重大专项项目（2025ZD0610102）

详细信息

作者简介:
刘林川（1998—），男，助理教授，博士(E-mail: liulinchuan@xjtu.edu.cn);范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

通讯作者:
范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

中图分类号: O302
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- 文章访问数: 11
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- PDF下载量: 2
- 被引次数: 0
出版历程
- 收稿日期: 2025-11-14
- 修回日期: 2026-03-13
- 网络出版日期: 2026-07-03
- 刊出日期: 2026-06-01

A Simplified Load Analysis Method and Load Characteristics of Coated Turbine Blades

Xi’an Key Laboratory of Extreme Environmental and Protection Technologies, School of Aerospace Engineering, Xi’an Jiaotong University, Xi’an 710049, P.R. China

摘要

摘要: 针对带涂层涡轮转子叶片跨尺度多层膜基系统建模复杂、载荷分析低效的问题，提出了一种基于壳导热模型与简化力学模型的高效载荷分析方法.在温度分析中引入等效热阻概念，在力学建模中建立了界面总应变张量一致性关系，避免了跨尺度界面引发的网格激增、畸变及计算发散问题.结果表明，与传统实体建模方法相比，该方法在保证温度与机械载荷计算误差均不超过5%的条件下，可使最小Jacobi比率提高约51.9%，单元数减少约80.8%，计算效率提升超过10倍.应用于带涂层涡轮叶片的分析结果显示，叶片温度高值区集中于叶尖，机械载荷高值区主要分布在叶根前缘，涂层载荷分布趋势与基体高度一致，体现了强耦合的响应特性.
- 带涂层涡轮叶片 /
- 热-力载荷 /
- 有限元模拟 /
- 壳导热模型 /
- 简化力学模型
Abstract: To address the challenges of complex modeling and low efficiency in load analysis of coated turbine blades with cross-scale multilayer coating-substrate systems, an efficient load analysis method based on a shell conduction model and a simplified mechanical model was proposed. The equivalent thermal resistance was introduced into the temperature analysis, and the consistency relation of the interfacial total strain tensors was established in the mechanical modeling, to effectively avoid mesh proliferation, distortion, and computational divergence induced by cross-scale interfaces. The results indicate that, compared with the conventional explicit modeling method, the proposed approach improves the minimum Jacobian ratio by approximately 51.9%, reduces the number of elements by about 80.8%, and enhances computational efficiency by more than an order of magnitude, while keeping temperature and mechanical load prediction errors below 5%. Furthermore, the analysis of coated turbine blades shows that, temperature hotspots are concentrated at the blade tip, while mechanical load hotspots are mainly distributed at the leading edge of the blade root. The load distribution in the coating exhibits a trend highly consistent with that of the substrate, reflecting a strongly coupled response behavior.
- coated turbine blade /
- thermo-mechanical load /
- finite element simulation /
- shell conduction model /
- simplified mechanical model

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参考文献(34)

[2]王铁军, 范学领, 丁秉钧, 等.热障涂层强度理论与检测技术[M]. 西安: 西安交通大学出版社, 2016. (WANG Tiejun, FAN Xueling, DING Bingjun, et al.Strength Theory and Testing Technology of Thermal Barrier Coatings[M]. Xi’an: Xi’an Jiaotong University Press, 2016. (in Chinese))

PADTURE N P, GELL M, JORDAN E H. Thermal barrier coatings for gas-turbine engine applications[J].Science,2002,296(5566): 280-284.

[3]LIU L, FU S, HU Z, et al. Thermo-mechanical analysis of TBC-film cooling system under high blowing ratio considering the effects of curvature[J].Surface and Coatings Technology,2023,470: 129826.

[4]柴怡君, 林晨, 李跃明. 考虑化学氧化效应时热障涂层氧化物的生长规律[J]. 应用数学和力学, 2015,36(4): 404-413. (CHAI Yijun, LIN Chen, LI Yueming. Growth trend of thermal grown oxide in TBCs under chemical oxidation effect[J].Applied Mathematics and Mechanics,2015,36(4): 404-413. (in Chinese))

[5]LIU L, WU J, HU Z, et al. Thermal analysis of turbine blades with thermal barrier coatings using virtual wall thickness method[J].Computer Modeling in Engineering & Sciences,2023,134(2): 1219-1236.

[6]WANG X M, HUI Y Z, HOU Y Y, et al. Direct investigation on high temperature tensile and creep behavior at different regions of directional solidified cast turbine blades[J].Mechanics of Materials,2019,136: 103068.

[7]RANI S, AGRAWAL A K, RASTOGI V. Failure analysis of a first stage IN738 gas turbine blade tip cracking in a thermal power plant[J].Case Studies in Engineering Failure Analysis,2017,8: 1-10.

[8]CHUNG H, SOHN H S, PARK J S, et al. Thermo-structural analysis of cracks on gas turbine vane segment having multiple airfoils[J].Energy,2017,118: 1275-1285.

[9]QU S, FU C M, DONG C, et al. Failure analysis of the 1st stage blades in gas turbine engine[J].Engineering Failure Analysis,2013,32: 292-303.

[10]KARGARNEJAD S, DJAVANROODI F. Failure assessment of Nimonic 80A gas turbine blade[J].Engineering Failure Analysis,2012,26: 211-219.

[11]WANG L, LI D C, YANG J S, et al. Modeling of thermal properties and failure of thermal barrier coatings with the use of finite element methods: a review[J].Journal of the European Ceramic Society,2016,36(6): 1313-1331.

[12]WANG Z, WANG D, LIU Z, et al. Numerical analysis on effects of inlet pressure and temperature non-uniformities on aero-thermal performance of a HP turbine[J].International Journal of Heat and Mass Transfer,2017,104: 83-97.

[13]MAIKELL J, BOGARD D, PIGGUSH J, et al. Experimental simulation of a film cooled turbine blade leading edge including thermal barrier coating effects[J].Journal of Turbomachinery,2011,133: 011014.

[14]LV B, JIN X, CAO J, et al. Advances in numerical modeling of environmental barrier coating systems for gas turbines[J].Journal of the European Ceramic Society,2020,40(9): 3363-3379.

[15]ZHU W, WANG J W, YANG L, et al. Modeling and simulation of the temperature and stress fields in a 3D turbine blade coated with thermal barrier coatings[J].Surface and Coatings Technology,2017,315: 443-453.

[16]JI Y, MA C, GE B, et al. Conjugate heat transfer investigation on the cooling performance of air cooled turbine blade with thermal barrier coating[J].Journal of Thermal Science,2016,25(4): 325-335.

[17]SHEN Q, LI S Z, YANG L, et al. Coupled mechanical-oxidation modeling during oxidation of thermal barrier coatings[J].Computational Materials Science,2018,154: 538-546.

[18]SONG J, QI H, SHI D, et al. Effect of non-uniform growth of TGO layer on cracking behaviors in thermal barrier coatings: a numerical study[J].Surface and Coatings Technology,2019,370: 113-124.

[19]ZHU W, CAI M, YANG L, et al. The effect of morphology of thermally grown oxide on the stress field in a turbine blade with thermal barrier coatings[J].Surface & Coatings Technology,2015,276: 160-167.

[20]LI B, FAN X, LI D, et al. Design of thermal barrier coatings thickness for gas turbine blade based on finite element analysis[J].Mathematical Problems in Engineering,2017,2017(1): 2147830.

[21]VO D T, MAI T D, KIM B, et al. Numerical study on the influence of coolant temperature, pressure, and thermal barrier coating thickness on heat transfer in high-pressure blades[J].International Journal of Heat and Mass Transfer,2022,189: 122715.

[22]BALINT D, HUTCHINSON J. An analytical model of rumpling in thermal barrier coatings[J].Journal of the Mechanics and Physics of Solids,2005,53(4): 949-973.

[23]BALINT D S, KIM S S, LIU Y F, et al. Anisotropic TGO rumpling in EB-PVD thermal barrier coatings under in-phase thermomechanical loading[J].Acta Materialia,2011,59(6): 2544-2555.

[24]JIANG J, MA X, WANG B. Stress analysis of the thermal barrier coating system near a cooling hole considering the free-edge effect[J].Ceramics International,2020,46(1): 331-342.

[25]VAUNOIS J R, DORVAUX J M, KANOUT P, et al. A new version of a rumpling predictive model in thermal barrier coatings[J].European Journal of Mechanics A,2013,42: 402-421.

[26]DRYEPONDT S, PORTER J R, CLARKE D R. On the initiation of cyclic oxidation-induced rumpling of platinum-modified nickel aluminide coatings[J].Acta Materialia,2009,57(6): 1717-1723.

[27]TOLPYGO V, CLARKE D. On the rumpling mechanism in nickel-aluminide coatings, part Ⅱ: characterization of surface undulations and bond coat swelling[J].Acta Materialia,2004,52(17): 5129-5141.

[28]SMETANKINA N V, POSTNYI O V, MERKULOVA A I, et al. Modeling of non-stationary temperature fields in multilayer shells with film heat sources[C]//2020 IEEE KhPI Week on Advanced Technology (KhPI Week). Kharkiv, Ukraine: IEEE, 2020: 242-246.

[29]BERGMAN T.Fundamentals of Heat and Mass Transfer[M]. Hoboken: John Wiley & Sons, 2011.

[30]LIU L, FAN X, CHU Z, et al. Thermo-mechanical loads and creep life assessment for coated turbine blades considering the influence of cooling hole blockage[J].Engineering Failure Analysis,2025,170: 109321.

[31]TRAEGER F, VAEN R, RAUWALD K H, et al. Thermal cycling setup for testing thermal barrier coatings[J].Advanced Engineering Materials,2003,5(6): 429-432.

[32]EVANS H E. Oxidation failure of TBC systems: an assessment of mechanisms[J].Surface and Coatings Technology,2011,206(7): 1512-1521.

[33]中国金属学会高温材料分会. 中国高温合金手册[M]. 北京: 中国标准出版社, 2012. (The High Temperature Materials Branch of The Chinese Society for Metals.China Superalloys Handbook[M]. Beijing: Standards Press of China, 2012. (in Chinese))

[34]CAI L, HE Y, WANG S, et al. Thermal-fluid-solid coupling analysis on the temperature and thermal stress field of a nickel-base superalloy turbine blade[J].Materials,2021,14(12): 3315.

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带涂层涡轮叶片载荷简化分析方法及载荷特性研究

doi: 10.21656/1000-0887.460201

作者简介:
刘林川（1998—），男，助理教授，博士(E-mail: liulinchuan@xjtu.edu.cn);范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

通讯作者:
范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

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A Simplified Load Analysis Method and Load Characteristics of Coated Turbine Blades

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留言板

带涂层涡轮叶片载荷简化分析方法及载荷特性研究

doi: 10.21656/1000-0887.460201

作者简介: 刘林川（1998—），男，助理教授，博士(E-mail: liulinchuan@xjtu.edu.cn);范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

通讯作者: 范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

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出版历程

A Simplified Load Analysis Method and Load Characteristics of Coated Turbine Blades

计量

出版历程

目录

作者简介:
刘林川（1998—），男，助理教授，博士(E-mail: liulinchuan@xjtu.edu.cn);范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).

通讯作者:
范学领（1978—），男，教授(通信作者. E-mail: fanxueling@mail.xjtu.edu.cn).