Overall Cooling Effectiveness and Mechanical Performance of Laminate-Thermal Barrier Coating Composite Structures

BAI Bo; ZHANG Jiawei; HAO Mingyang; LI Zhigang; LI Jun

doi:10.7652/xjtuxb202603010

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Overall Cooling Effectiveness and Mechanical Performance of Laminate-Thermal Barrier Coating Composite Structures

更新时间：2026-03-09

- Overall Cooling Effectiveness and Mechanical Performance of Laminate-Thermal Barrier Coating Composite Structures
- Journal of Xi'an Jiaotong University Vol. 60, Issue 3, Pages: 97-109(2026)
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202603010
  CLC： TK474.4
- Received：16 April 2025，
  
  Published：10 March 2026
- 稿件说明：
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BAI Bo, ZHANG Jiawei, HAO Mingyang, et al. Overall Cooling Effectiveness and Mechanical Performance of Laminate-Thermal Barrier Coating Composite Structures[J]. Journal of Xi'an Jiaotong University, 2026, 60(3): 97-109.
DOI：

BAI Bo, ZHANG Jiawei, HAO Mingyang, et al. Overall Cooling Effectiveness and Mechanical Performance of Laminate-Thermal Barrier Coating Composite Structures[J]. Journal of Xi'an Jiaotong University, 2026, 60(3): 97-109. DOI： 10.7652/xjtuxb202603010.

摘要

为阐明层板-热障涂层（TBC）复合结构气热性能与应力分布特征，实现层板冷却结构与TBC高效耦合目标，采用共轭传热模型，提出了复合结构流-固-力耦合数值预测方法，系统研究了气膜板厚度（

0.8

，1.0

，1.2

，

为气膜孔直径）与TBC厚度（

TBC

0.6

，0.8

，1.0

）对复合结构综合冷却特性和应力分布的影响。研究结果表明：复合结构TBC表面和金属基体表面综合冷却效率对气膜板厚度变化不敏感，不同气膜板厚度下复合结构综合冷却效率差异小于1.0%。增加TBC厚度可以显著增强复合结构金属基体表面综合冷却效率，在

TBC

为1.0

时，相较于参考工况综合冷却效率增幅约为15.6%。气膜板厚度与TBC厚度对复合结构力学性能影响具有拮抗效应，随着

和

TBC

增加，等效应力降幅和等效应力增幅分别超过10.0%和23.5%。复合结构中气膜孔出口、金属基体/TBC交界面和气膜孔入口附近存在应力集中现象，气膜孔前缘应力沿径向呈W型分布，在金属基体/TBC交界面处出现等效应力峰值。增加气膜板厚度可以改善金属基体内部力学性能，喷涂较厚的TBC可以缓解金属基体/TBC交界面应力集中，降低TBC剥落风险，但会显著增强气膜孔出口附近应力水平（最大等效应力超过1 000 MPa），因此建议在层板-TBC复合结构设计中采用较厚的气膜板（

=1.2

）和喷涂合适厚度TBC（

TBC

=0.8

）的方案。

Abstract

To elucidate the aero-thermal performance and stress distribution characteristics of laminate-thermal barrier coating (TBC) composite structures and achieve efficient coupling between laminate cooling structures and TBC

a conjugate heat transfer model is adopted to establish a fluid-solid-force coupled numerical prediction method.The effects of film-cooling plate thickness (

=0.8

1.0

1.2

)and TBC thickness (

TBC

=0.6

0.8

1.0

)on the overall cooling characteristics and stress distribution of the composite structure are systematically investigated.The results show that the overall cooling effectiveness on both the TBC surface and the metal substrate surface is insensitive

to changes in the film-cooling plate thickness

with differences in overall cooling effectiveness under different

values being less than 1.0%.Increasing the TBC thickness significantly enhances the overall cooling effectiveness of the metal substrate surface.At

TBC

=1.0

the overall cooling effectiveness increases by approximately 15.6% compared to the reference case.The film-cooling plate thickness and the TBC thickness exhibit antagonistic effects on the mechanical performance of the composite structure.As

and

TBC

increase

the reduction in equivalent stress and the increase in equivalent stress exceed 10.0% and 23.5%

respectively.Stress concentration occurs near the film-cooling hole exit

the metal substrate/TBC interface

and the film-cooling hole inlet in the composite structure.The stress distribution along the radial direction at the leading edge of the film-cooling hole shows a W-shaped profile

with a peak equivalent stress appearing at the metal substrate/TBC interface. Increasing the film-cooling plate thickness improves the mechanical performance within the metal substrate

while applying a thicker TBC alleviates stress concentration at the metal substrate/TBC interface and reduces the risk of TBC spallation.However

a thicker TBC significantly elevates the stress level near the film-cooling hole exit (maximum equivalent stress exceeding 1 000 MPa).Therefore

it is recommended in laminate-TBC composite structure design to adopt a thicker film-cooling plate (

=1.2

)along with an appropriately thick TBC coating (

TBC

=0.8

关键词

Keywords

references

National Academies of Sciences, Engineering, and Medicine, Division on Engineering and Physical Sciences, Aeronautics and Space Engineering Board, et al. Advanced technologies for gas turbines[M]. Washington, USA：National Academies Press, 2020.

BUNKER R S.Evolution of turbine cooling[C]//ASME Turbo Expo 2017：Turbomachinery Technical Conference and Exposition.New York, USA：ASME, 2017：V001T51A001 .

任静，李雪英，郭欣欣，等.燃气涡轮高效冷却技术及设计方法发展趋势[J].清华大学学报（自然科学版），2022，62（4）：794-801 .

REN Jing，LI Xueying，GUO Xinxin，et al. Development trends in high-efficiency gas turbine cooling methods[J].Journal of Tsinghua University（Science and Technology），2022，62（4）：794-801.

张垲垣，栗智宇，李志刚，等.曲面双层壁结构的内外复合流动及综合冷却特性数值研究[J].西安交通大学学报，2025，59(2)：50-60.

ZHANG Kaiyuan，LI Zhiyu，LI Zhigang，et al. Numerical investigation of internal and external flow interaction and overall cooling characteristics of curvature double-wall structures[J].Journal of Xi’an Jiaotong University，2025，59(2)：50-60.

李威宏.燃机透平薄壁叶片冷却结构的对流与耦合传热机制研究[D].北京：清华大学，2018：83-100.

GU Huaduo, LIANG Dong, DUAN Penghao, et al. Aerothermal characteristics of thin double-wall effusion cooling systems with novel slot holes and cellular architectures for gas turbines[J].Aerospace Science and Technology, 2023, 140：108441.

GU Huaduo, ZHOU Deli, DU Kun, et al. Overall cooling characteristics of double-wall effusion system considering material selections and hole arrangements[J]. International Journal of Heat and Mass Transfer, 2023, 216：124599.

程想，丁俣中，万红牛，等.冲击孔位置对涡轮叶片冲击/气膜复合冷却特性影响的实验研究[J].西安交通大学学报，2023，57(12)：59-71 .

CHENG Xiang，DING Yuzhong，WAN Hongniu，et al. Experimental investigation on effects of the impingement hole position on impingement/film cooling characteristics of turbine vanes[J].Journal of Xi’an Jiaotong University，2023，57(12)：59-71.

NGETICH G C, MURRAY A V, IRELAND P T, et al. A three-dimensional conjugate approach for analyzing a double-walled effusion-cooled turbine blade[J]. Journal of Turbomachinery, 2019, 141(1)：011002.

SAKAI E, TAKAHASHI T, AGATA Y.Experimental study on effects of internal ribs and rear bumps on film cooling effectiveness[J].Journal of Turbomachinery, 2013, 135(3)：031025.

季钧，张靖周，王春华.稀疏孔阵层板冷却结构的主要参数影响数值研究[J].南京航空航天大学学报，2019，51(6)：848-856.

JI Jun，ZHANG Jingzhou，WANG Chunhua.Numerical investigation on influence of main structural parameters in lamilloy cooling configuration with a sparse hole array[J].Journal of Nanjing University of Aeronautics & Astronautics，2019，51(6)：848-856.

KONG Dehai, MA Zhenyuan, LI Wei, et al. Effect of rib blockage ratio and arrangements on impingement heat transfer in double-wall cooling[J].ASME Journal of Heat and Mass Transfer, 2023, 145 (9 )：091001 .

LUAN Yigang, ZHANG Limin, WU Xue, et al. Numerical research for the influence of cylindrical ribs and inclined mainstream on double wall cooling configurations[J].International Journal of Thermal Sciences, 2024, 197：108841.

王一，汪翔宇，李家龙，等.多孔介质扰流柱对双层壁冷却系统性能影响的数值研究[J].西安交通大学学报，2025，59(2)：61-72.

WANG Yi，WANG Xiangyu，LI Jialong，et al. Numerical study on effects of pin fin with porous medium on performance of double-wall cooling system[J]. Journal of Xi’an Jiaotong University，2025，59 (2)：61-72.

MURRAY A V, IRELAND P T, ROMERO E.Development of a steady-state experimental facility for the analysis of double-wall effusion cooling geometries[J]. Journal of Turbomachinery, 2019, 141(4)：041008.

MURRAY A V, IRELAND P T, ROMERO E.Experimental and computational methods for the evaluation of double-wall, effusion cooling systems[J]. Journal of Turbomachinery, 2020, 142(11)：111003.

YAO Ran, LIU Taolue, HUANG Xin, et al. Multiobjective design of laminated cooling configuration applied in gas turbine based on fuzzy grey relational analysis[J].International Journal of Heat and Mass Transfer, 2023, 207：124035 .

宋伟.全双层壁燃气涡轮导向叶片数值及实验研究[D].合肥：中国科学技术大学，2024：39-56.

DAVIDSON F T, KISTENMACHER D A, BOGARD D G.Film cooling with a thermal barrier coating：round holes, craters, and trenches[J].Journal of Turbomachinery, 2014, 136(4)：041007.

DAVIDSON F T, DEES J E, BOGARD D G.Anexperimental study of thermal barrier coatings and film cooling on an internally cooled simulated turbine vane[C]//ASME 2011 Turbo Expo：Turbine Technical Conference and Exposition.New York, USA：ASME, 2011：559-570.

胡冰城，王建华，徐华昭，等.具有热障涂层的导向叶片耦合数值研究[J].航空动力学报，2017，32 (10)：2394-2402.

HU Bingcheng，WANG Jianhua，XU Huazhao，et al. Numerical investigation of a thermal barrier coated vane using conjugate heat transfer approach[J].Journal of Aerospace Power，2017，32(10)：2394-2402.

MENSCH A, THOLE K A.Overall effectiveness and flowfield measurements for an endwall with nonaxisymmetric contouring[J].Journal of Turbomachinery, 2016, 138(3)：031007.

HUANG Xin, PU Jian, WANG Jianhua, et al. Sensitivity analysis of internal layout and coating thickness to overall cooling performances of laminated cooling configurations with surface thermal barrier coatings[J].Applied Thermal Engineering, 2020, 181：116020.

ELMUKASHFI E, MURRAY A V, IRELAND P T, et al. Analysis of the thermomechanical stresses in double-wall effusion cooled systems[J].Journal of Turbomachinery, 2020, 142(5)：051002.

SKAMNIOTIS C, COCKS A C F.Designing against severe stresses at compound cooling holes of double wall transpiration cooled engine components[J].Aerospace Science and Technology, 2021, 116：106856.

ZOU Yifan, YOU Ruquan, LI Haiwang, et al. Influence of blowing ratio and geometric parameters on cooling performance and thermal stress of a double wall structure[J].Thermal Science and Engineering Progress, 2024, 48：102420.

WANG Chen, ZHANG Jingzhou, WANG Chunhua, et al. Multi-optimization of a specific laminated cooling structure for overall cooling effectiveness and pressure drop[J].Numerical Heat Transfer：Part A Applications, 2021, 79(3)：195-221.

COURTIS M, SKAMNIOTIS C, COCKS A, et al. Coupled aerothermal-mechanical analysis in single crystal double wall transpiration cooled gas turbine blades with a large film hole density[J].Applied Thermal Engineering, 2023, 219(Part A)：119329.

JIANG Jishen, JIANG Lingxin, CAI Zhenwei, et al. Numerical stress analysis of the TBC-film cooling system under operating conditions considering the effects of thermal gradient and TGO growth[J].Surface and Coatings Technology, 2019, 357：433-444.

CHEN Xiaohu, LI Jiao, LONG Yun, et al. A conjugate heat transfer and thermal stress analysis of filmcooled superalloy with thermal barrier coating[C]//ASME Turbo Expo 2020：Turbomachinery Technical Conference and Exposition.New York, USA：ASME, 2020：V07BT12A074.

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

史天杰，张鑫，彭浩然，等.热障涂层材料体系研究现状及展望[J].热喷涂技术，2023，15(2)：1-12.

SHI Tianjie，ZHANG Xin，PENG Haoran，et al. Research status and prospect of thermal barrier coating materials system[J].Thermal Spray Technology，2023，15(2)：1-12.

BUNKER R S.The effects of manufacturing tolerances on gas turbine cooling[J].Journal of Turbomachinery, 2009, 131(4)：041018.

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