考虑精铸变形的涡轮叶片气膜冷却效率灵敏度计算方法研究

尤鑫添; 董一巍; 刘松; 吴超林; 郭文; 龚雨晗

doi:10.13433/j.cnki.1003-8728.20240023

考虑精铸变形的涡轮叶片气膜冷却效率灵敏度计算方法研究

doi: 10.13433/j.cnki.1003-8728.20240023

尤鑫添^1,,
董一巍^1, ,,
刘松²,
吴超林^{1, 2},
郭文²,
龚雨晗¹

1.
厦门大学航空航天学院, 福建厦门 361102
2.
中国航发四川燃气涡轮研究院, 成都 610500

基金项目:

国家科技重大专项 J2019-II-0022-0043

国家科技重大专项 J2019-VII-0013-0153

国家自然科学基金项目 51705440

福建省自然科学基金项目 2019J01044

航空科学基金项目 20230003068002

航空科学基金项目 20170368001

福建省中科院STS计划配套院省合作重大项目 2022T3071

详细信息

作者简介:
尤鑫添, 硕士研究生, 862149938@qq.com

通讯作者:
董一巍, 副教授, 博士生导师, 博士, yiweidong@xmu.edu.cn

中图分类号: V231.1
计量
- 文章访问数: 767
- HTML全文浏览量: 6
- PDF下载量: 2
- 被引次数: 0
出版历程
- 收稿日期: 2023-10-07
- 刊出日期: 2024-07-25

Calculation Method of Turbine Blade Cooling Efficiency Sensitivity Considering Deformation of Investment Casting

YOU Xintian^1
,,
DONG Yiwei^{1
, ,},
LIU Song²,
WU Chaolin^{1, 2},
GUO Wen²,
GONG Yuhan¹

1.
School of Aerospace Engineering, Xiamen University, Xiamen 361102, Fujian, China
2.
AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China

摘要

摘要: 精铸加工使得涡轮叶片几何结构与设计之间产生随机性偏差, 这一偏差对叶片气膜冷却效率造成不确定性影响。涡轮叶片外形偏差的不确定性是几何层面的小扰动问题。本文通过精铸模拟建立了涡轮叶片精铸变形模型。基于PIV与数值模拟建立了适用于流热耦合计算的Realizable k-epsilon湍流模型, 建立了考虑叶片变形的气膜冷却效率灵敏度计算方法, 计算了涡轮叶片的气膜冷却效率随吹风比变化的灵敏度。结果表明: 涡轮叶片精铸产生的变形越大, 对原有气膜冷却效率的损失越大。叶片整体平均形变0.25 mm使得整体气膜冷却效率损失约5%, 局部形变如叶尖叶片后缘处的0.70 mm可使叶尖平均气膜冷却效率损失约8%。由灵敏度分析确定的精铸后气膜冷却效率相对误差较明显, 达到了1.62%。
- 涡轮叶片 /
- 精铸变形 /
- CFD仿真 /
- 气膜冷却效率 /
- 灵敏度
Abstract: The precision casting process results in a random deviation between the turbine blade geometry and the design, which has an uncertain effect on the blade air cooling efficiency. The uncertainty of turbine blade contour deviation is a minor disturbance problem in geometry. A model for deformation in the investment casting of the turbine blade is established by using the investment casting simulation. According to PIV and the numerical simulation, a realizable k-epsilon turbulence model for fluid-heat coupling calculation was established. A sensitivity calculation method of cooling efficiency considering blade deformation was established, and the sensitivity variation of the turbine blade air-cooling efficiency with the blow ratio was calculated. The results show that the greater the deformation of turbine blades is, the greater the loss of the original cooling efficiency. The overall average blade deformation of 0.25 mm makes the overall air-cooling efficiency loss of about 5%, and the local deformation such as 0.70 mm at the rear edge of the blade make the average air-cooling efficiency to be a loss of about 8%.
- turbine blade /
- investment casting deformation /
- cfd simulation /
- film cooling efficiency /
- sensitivity

HTML全文

图 1 动叶浇注系统凝固过程温度场云图

Figure 1. Temperature field during solidification of turbine blade pouring system

下载: 全尺寸图片幻灯片

图 2 叶片的叶盆和叶背形变量分布云图

Figure 2. Cloud map of deformation distribution of leaf basin and leaf back

下载: 全尺寸图片幻灯片

图 3 排沙孔中径位置

Figure 3. Location of the turbine blade sand discharge hole

下载: 全尺寸图片幻灯片

图 4 不同模型特征位置流体流速对比

Figure 4. Flow rates at characteristic locations of different models

下载: 全尺寸图片幻灯片

图 5 网格无关性验证

Figure 5. Grid independence verification

下载: 全尺寸图片幻灯片

图 6 不同吹风比下精铸前后叶片表面气膜冷却效率对比

Figure 6. Comparison of air cooling efficiency of blade surface before and after investment casting under different blowing ratios

下载: 全尺寸图片幻灯片

图 7 所选叶尖部位

Figure 7. The chosen turbine blade tip

下载: 全尺寸图片幻灯片

图 8 不同吹风比下精铸前后叶片叶尖表面气膜冷却效率对比

Figure 8. Comparison of the air cooling efficiency of blade tip surface before and after investment casting under different blowing ratios

下载: 全尺寸图片幻灯片

图 9 测量点分布示意

Figure 9. Distribution of measuring points of turbine blade

下载: 全尺寸图片幻灯片

图 10 精铸前气膜冷却效率灵敏度变化

Figure 10. Sensitivity change of gas film cooling efficiency before investment casting

下载: 全尺寸图片幻灯片

图 11 精铸后气膜冷却效率灵敏度变化

Figure 11. Sensitivity change of gas film cooling efficiency after investment casting

下载: 全尺寸图片幻灯片

表 1 基于灵敏度分析的气膜冷却效率偏差

Table 1. Efficiency deviation of gas film cooling based on sensitivity analysis

叶片	CFD	伴随方法	偏差/%
设计模型	0.356 17	-	-
精铸模型	0.347 77	0.342 15	1.62

下载: 导出CSV

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