Research on the Thermal Fatigue of Aero-Engine Combustor under Fluid-Structure Interaction

doi:10.7652/xjtuxb201805021

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Research on the Thermal Fatigue of Aero-Engine Combustor under Fluid-Structure Interaction

更新时间：2025-07-09

- Research on the Thermal Fatigue of Aero-Engine Combustor under Fluid-Structure Interaction
- Vol. 52, Issue 5, Pages: 149-156(2018)
- 作者机构：
  
  1. 天津大学内燃机燃烧学国家重点实验室,天津,300354
  2. 天津大学仁爱学院机械工程系,天津,301636
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201805021
  CLC： V232.6
- Online First：10 May 2018，
  
  Published：2018
- 稿件说明：
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Research on the Thermal Fatigue of Aero-Engine Combustor under Fluid-Structure Interaction[J]. 2018, 52(5): 149-156.
DOI：

Research on the Thermal Fatigue of Aero-Engine Combustor under Fluid-Structure Interaction[J]. 2018, 52(5): 149-156. DOI： 10.7652/xjtuxb201805021.

摘要

针对某航空发动机在服役过程中出现的燃烧室基体开裂现象

研究了航空发动机的燃烧室热疲劳。通过三坐标扫描逆向建模获得了航空发动机的燃烧室三维模型

选取满足周期性对称条件的1/10扇形段燃烧室作为计算域

考虑流体域与固体域之间的相互作用

建立了某航空发动机燃烧室湍流燃烧流固耦合模型

对典型工况下燃烧室内流场进行了模拟

获得了燃烧室基体及热障涂层的温度分布

并对热障涂层外表面温度场与实际服役燃烧室热障涂层宏观样貌进行对比

验证了流固耦合计算的准确性; 对燃烧室基体进行了非线性静力学分析

获得了燃烧室基体的应变分布

应变最大位置与燃烧室基体实际开裂位置对应; 通过Manson-Coffin公式及线性累积损伤理论

计算得到了在典型工作循环下危险点的寿命。结果表明

随着发动机负荷的上升

燃烧室基体温度逐渐升高

在冷热气流的冲击下

掺混孔下游区域温度分布不均匀

使得该区域塑性应变较大从而导致掺混孔区域的低周疲劳破坏

危险点的最低寿命典型起落循环数为7 126。

Abstract

Thermal fatigue study on an aero-engine combustor is carried out for the cracking failure of combustor during its service period. A three-dimensional model of the aero-engine combustor is obtained by three-coordinate scanning reverse modeling

an 1/10 sector of the combustor satisfying the periodic boundary condition is chosen as the computational domain. Considering the interaction between the fluid and solid

a fluid-structure interaction model for the turbulent combustion of the aero-engine combustor is established to simulate the flow field at typical conditions

hence the temperature distribution of the combustor and thermal barrier coating is obtained. The accuracy of the fluid-structure interaction simulation is verified through the comparison between the surface temperature distribution and the macroscopic appearance of the thermal barrier coating of a combustor in service. Based on the results of simulation

nonlinear static analysis is carried out to obtain the plastic strain distribution and hence the maximum strain position corresponding to the actual cracking position of the combustor. Based on Manson-Coffin formula and linear damage rule

the fatigue life of dangerous positions under typical working cycle is calculated. The results show that the temperature of combustor substrate increases gradually with the increasing of engine load

and that the temperature distribution in the downstream region of mixing holes is inhomogeneous under the impact of cold-hot air flows

resulting in large plastic strain and low-cycle fatigue damage. The fatigue life of the dangerous positions under typical working cycle is calculated to be 7 126 cycles.

关键词

Keywords

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