Investigations on the Aerothermal and Mechanical Performances of Laminate/TBC Composite Geometry

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

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Investigations on the Aerothermal and Mechanical Performances of Laminate/TBC Composite Geometry

更新时间：2026-01-02

- Investigations on the Aerothermal and Mechanical Performances of Laminate/TBC Composite Geometry
- JOURNAL OF XI’AN JIAOTONG UNIVERSITY (2026)
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，陕西西安
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK474.4
- Received：16 April 2025，
  
  Revised：2025-08-19，
  
  Accepted：03 December 2025，
- 稿件说明：
移动端阅览
BAI Bo, ZHANG Jiawei, HAO Mingyang, et al. Investigations on the Aerothermal and Mechanical Performances of Laminate/TBC Composite Geometry[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026.
DOI：

BAI Bo, ZHANG Jiawei, HAO Mingyang, et al. Investigations on the Aerothermal and Mechanical Performances of Laminate/TBC Composite Geometry[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026. DOI：

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，本文采用共轭传热模型，发展了复合结构流-固-力耦合数值预测方法，系统研究了气膜板厚度（

= 0.8

、1.0

和1.2

）与TBC厚度（

TBC

= 0.6

、0.8

和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效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效差异小于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效，在

TBC

= 1.0

时，综合冷效增幅约为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，等效应力降幅和增幅分别超过10%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，气膜孔前缘沿径向应力呈“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1000 MPa），因此本文建议在层板/TBC复合结构设计中采用较厚的气膜板（本文中

= 1.2

）和喷涂合适厚度TBC（本文中

TBC

= 0.8

）的方案。

Abstract

To clarify the aerothermal performance and stress characteristics of laminate/TBC composite geometry and achieve the goal of efficient coupling between laminate cooling structures and thermal barrier coatings (TBC)

a conjugate heat transfer model was adopted to develop the numerical method for fluid-solid-mechanical coupling in composite geometry in this paper. This study systematically analyzes the impacts of film plate thickness (

= 0.8

1.0

and 1.2

) and TBC thickness (

TBC

= 0.6

0.8

and 1.0

) on the overall cooling performance and stress distributions of composite geometry. Results indicate that overall cooling effectiveness of both TBC surface and metal substrate surface in composite geometry is insensitive to film plate thickness variations

with the magnitudes less than 1.0%. The overall cooling effectiveness of metal substrate surface significantly enhances as the TBC thickness increases

with an improvement of approximately 15.6% at

TBC

= 1.0

. The antagonistic impacts on the mechanical properties are observed between film plate thickness and TBC thickness in composite geometry. With increasing

and

TBC

the equivalent stress decreases by over 10% and increases by over 23.5%

respectively. In composite geometry

the stress concentration phenomenon is noticed in these regions of film hole exits

metal substrate/TBC interface and film hole inlets. The radial stress along the leading edge of film holes presents a “W”-type pattern and the peak equivalent stress is obtained at the metal substrate/TBC interface. Increasing film plate thickness can improve the mechanical properties within the metal substrate

while applying a thicker TBC can alleviate stress concentration at the metal substrate/TBC interface and reduce TBC spallation risks. However

a thicker TBC significantly intensifies stress levels near film hole exits (more than 1000 MPa). Therefore

the design scheme with a thicker film plate (

= 1.2

in this paper) and an adequate thickness of TBC (

TBC

= 0.8

in this paper) is recommended in the laminate/TBC composite geometry.

关键词

Keywords

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Related Institution

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