面向热障涂层和气膜冷却的快速耦合热分析方法

周源昊; 吕东; 刘英实; 张晓鑫; 徐景亮

doi:10.13224/j.cnki.jasp.20230820

面向热障涂层和气膜冷却的快速耦合热分析方法

doi: 10.13224/j.cnki.jasp.20230820

周源昊^1,,
吕东^1,*, ,,
刘英实¹,
张晓鑫¹,
徐景亮²

1.
大连理工大学能源与动力学院涡轮叶片创新实验室，辽宁大连 116024
2.
中国航发沈阳发动机研究所，沈阳 110015

基金项目: 航空发动机气动热力重点实验室基金（2021-JCJQ-LB-062-0408）

详细信息

作者简介:
周源昊（1999-），男，硕士生，主要从事涡轮叶片冷却研究。E-mail：zhouyh@mail.dlut.edu.cn

通讯作者:
吕东（1979-），男，教授、博士生导师，博士，主要从事涡轮叶片冷却技术研究。E-mail：ld@dlut.edu.cn

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2023-12-27
- 网络出版日期: 2024-06-19

Rapid thermal analysis method for film cooling coupled with thermal barrier coatings

1.
Innovation Lab of Gas Turbine Blade，School of Energy and Power Engineering，Dalian University of Technology，Dalian Liaoning 116024，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
面向涡轮叶片的冷却设计和分析问题，建立并初步验证了一种热障涂层和气膜冷却耦合的快速热分析方法。该方法首先基于金属区域导热流线的形貌，提出将此传热过程分解为相互间绝热的三类，以此降低方程构建的难度。又进一步采用拓扑转化方法，将上述复杂的三维传热过程比拟为了一维的均匀平板或圆管扇形段，最终推导得到了一组共计40个直接计算公式，实现了对目标壁面加权平均温度的快速求解。该方法可用于分析流动和传热工况、气膜孔和热障涂层几何结构，以及涂层和金属基体物性参数等对壁温的影响。以多种热障涂层涂敷方式和吹风比M工况下的三维热分析结果作为基准，对方法准确性进行了校验，所得特征壁温的相对误差δ均在±1.25%之间，可满足工程应用需求。
- 涡轮叶片 /
- 热障涂层 /
- 气膜冷却 /
- 热分析方法 /
- 拓扑转化
Abstract:
In order to efficiently design and analyze the turbine blade cooling structures, a rapid thermal analysis method for film cooling coupled with thermal barrier coatings (TBC) was established and basically verified. Based on the morphologies of the conductive heat flow streamlines in the metal region, the heat transfer processes were separated into three parts of mutual adiabatic, so as to reduce the difficulties of equation construction. Topologically transforming methods were applied, thus the complicated 3D heat transfer processes were translated into 1D ones like flat plates or fan-shaped segments with uniform wall thickness. A set of 40 direct calculation formulas were derived accordingly, which achieves a rapid solution of the weighted average temperature at the objective walls. Many effects on the wall temperature could be analyzed by this method, such as the flow and heat transfer conditions, the geometries of both film cooling hole and TBC, and also the material properties of them. The accuracy of the method was investigated by comparing its results with the fiducial ones obtained from 3D simulations. The relative error (δ) of these wall temperatures were within ±1.25% considering various TBC coverage schemes and blowing ratios (M) operating conditions, which met the requirements of engineering applications.
- turbine blade /
- thermal barrier coatings /
- film cooling /
- thermal analysis method /
- topological transformation

HTML

图 1 仿真模型和边界条件

Figure 1. Simulation model and boundary conditions

下载: 全尺寸图片幻灯片

图 2 3类热流流线形貌图

Figure 2. Morphology of three types of heat flow streamlines

下载: 全尺寸图片幻灯片

图 3 3类传热过程的拓扑转化

Figure 3. Topological transformation of three types of heat transfer process

下载: 全尺寸图片幻灯片

图 4 壁温的三维和一维计算结果

Figure 4. Wall temperature results by 3D and 1D calculation methods

下载: 全尺寸图片幻灯片

图 5 δ随M的变化趋势图

Figure 5. Variation of δ with M

下载: 全尺寸图片幻灯片

表 1 计算参数

Table 1. Parameters of computation

参数类型	变量	数值
几何结构	l/mm	35
	b/mm	2
	H/mm	2
	D/mm	1
	l_h/mm	2
	β/（°）	40
	H_TBC/mm	0.3
	燃气覆盖区热障涂层	有
	气膜覆盖区热障涂层	无
工况条件	M	1
	T_g/K	2000
	T_c/K	1000
	α_g/（W/（m²·K））	1400
	$\alpha_{\mathrm{g}}' $/（W/（m²·K））	1157.03
	α_c1/（W/（m²·K））	1200
	$\alpha_{\mathrm{c1}}' $/（W/（m²·K））	1016.95
	α_c2/（W/（m²·K））	1194.07
	α_c3/（W/（m²·K））	500
物性参数	λ_s/（W/（m·K））	20
物性参数	λ_TBC/（W/（m·K））	2

下载: 导出CSV

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