叶顶喷气对不同叶冠结构的带冠涡轮叶片气动性能影响的试验与数值研究

吴磊; 屈彬; 蒋振宇; 周成; 高杰

doi:10.13224/j.cnki.jasp.20220927

叶顶喷气对不同叶冠结构的带冠涡轮叶片气动性能影响的试验与数值研究

doi: 10.13224/j.cnki.jasp.20220927

吴磊^1,,
屈彬²,
蒋振宇¹,
周成¹,
高杰^1,*, ,

1.
哈尔滨工程大学动力与能源工程学院，哈尔滨 150001
2.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 黑龙江省优秀青年科学基金（YQ2020E024）；国家自然科学基金（51979052）；国家科技重大专项（2017-Ⅲ-0010-0036）

详细信息

作者简介:
吴磊（1998-），男，硕士生，主要从事叶轮机械气动热力学研究

通讯作者:
高杰（1985-），男，教授、博士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：gaojie_d@hrbeu.edu.cn

中图分类号: V232.4
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- 被引次数: 0
出版历程
- 收稿日期: 2022-12-02
- 网络出版日期: 2025-02-26

Experimental and numerical study on the influence of tip injection on the aerodynamic performance of shrouded turbine blades with different shroud structures

WU Lei^1
,,
QU Bin²,
JIANG Zhenyu¹,
ZHOU Cheng¹,
GAO Jie^{1,*
, ,}

1.
College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China
2.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
针对叶冠结构的改进和优化研究是燃气轮机研究领域的重要方向之一，为了研究叶顶喷气对带冠涡轮叶片气动性能的影响，分别对全冠、部分冠、尾缘切削优化冠和前尾缘均切削优化冠这4种冠型开展平面叶栅试验研究，同时结合部分数值计算结果。通过对比分析4种试验冠在有无叶顶喷气时的相关气动参数，结果表明：当叶顶有冷气喷射时，可以改善叶冠容腔进出口的泄漏流动，降低气动损失；同时，尾缘切削优化冠的总压损失平均值相比于部分冠低24.8%，比前尾缘均切削优化冠低6.87%，尾缘切削优化冠相比于部分冠和前尾缘均切削的优化冠拥有更好的气动性能。
- 带冠涡轮叶片 /
- 不同叶冠结构 /
- 叶顶喷气 /
- 端部流动 /
- 气动性能
Abstract:
The study on the improvement and optimization of shroud structure is one of the important directions in the field of gas turbine research. In order to study the influence of tip injection on the aerodynamic performance of shrouded turbine blades, four kinds of shrouds, including full shroud, partial shroud, trailing edge cutting optimized shroud and front and trailing edge cutting optimized shroud, were studied by plane cascade experiment. By comparing and analyzing relevant aerodynamic parameters of the four experimental shrouds with or without tip injection, the results showed that when the tip had cold air injection, the leakage flow at the inlet and outlet of the shroud cavity can be improved and the aerodynamic loss can be reduced. At the same time, the average total pressure loss of the trailing edge cutting optimized shroud was 24.8% lower than that of the partial shroud and 6.87% lower than that of the front and trailing edge cutting optimized shroud. The trailing edge cutting optimized shroud had better aerodynamic performance than the partial shroud and the front and trailing edge cutting optimized shroud.
- shrouded turbine blade /
- different shroud structures /
- tip air injection /
- endwall flow /
- aerodynamic performance

HTML

图 1 带冠叶栅换热试验台

Figure 1. Heat transfer experiment rig with shrouded cascade

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图 2 气源系统

Figure 2. Air supply system

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图 3 科索压缩机

Figure 3. Koso compressor

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图 4 带冠涡轮叶片实物图

Figure 4. Physical drawing of shrouded turbine blade

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图 5 不同结构叶冠试验件

Figure 5. Different structure shroud experiment pieces

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图 6 计算网格

Figure 6. Computational grid

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图 7 泄漏流量网格无关性验证图

Figure 7. Leakage flow grid independence verification diagram

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图 8 全冠有无叶顶喷气时50%叶高压力系数分布

Figure 8. Distribution of high pressure coefficient of 50% blade span with or without tip injection in full shroud

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图 9 部分冠有无叶顶喷气时50%叶高压力系数分布

Figure 9. Distribution of high pressure coefficient of 50% blade span with or without tip injection in partial shroud

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图 10 尾缘切削优化冠有无叶顶喷气时50%叶高压力系数分布

Figure 10. Distribution of high pressure coefficient of 50% blade span with or without tip injection in trailing edge cutting optimized shroud

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图 11 前尾缘均切削优化冠有无叶顶喷气时50%叶高压力系数分布

Figure 11. Distribution of high pressure coefficient of 50% blade span with or without tip injection in front and trailing edge cutting optimized shroud

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图 12 全冠容腔中流线分布图

Figure 12. Distribution diagram of streamline in full shroud cavity

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图 13 部分冠容腔中流线分布图

Figure 13. Distribution diagram of streamline in partial shroud cavity

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图 14 尾缘切削优化冠容腔中流线分布图

Figure 14. Distribution diagram of streamline in shroud cavity optimized by trailing edge cutting

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图 15 前尾缘均切削优化冠容腔中流线分布图

Figure 15. Distribution diagram of streamline in shroud cavity optimized by leading edge and trailing edge cutting

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图 16 4种试验冠在叶顶有无喷气出口总压损失对比

Figure 16. Comparison of total pressure loss of four experimental shrouds with or without jet outlet at blade tip

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图 17 4种试验冠在叶顶有无喷气出口气流角对比

Figure 17. Comparison of airflow angle of four experimental shrouds with or without jet outlet at blade tip

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图 18 全冠出口总压损失系数分布

Figure 18. Distribution of total pressure loss coefficient of full shroud outlet

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图 19 部分冠出口总压损失系数分布

Figure 19. Distribution of total pressure loss coefficient of partial shroud outlet

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图 20 尾缘切削优化冠出口总压损失系数分布

Figure 20. Distribution of total pressure loss coefficient of trailing edge cutting optimized shroud outlet

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图 21 前尾缘均切削优化冠出口总压损失系数分布

Figure 21. Distribution of total pressure loss coefficient of shroud outlet optimized by leading edge and trailing edge cutting

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图 22 4个试验冠出口总压损失径向分布

Figure 22. Radial distribution of total pressure loss at outlet of four experimental shrouds

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图 23 4个试验冠出口气流角径向分布

Figure 23. Radial distribution of outlet airflow angle of four experimental shrouds

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表 1 不同叶冠结构总压损失系数对比

Table 1. Comparison of total pressure loss coefficients of different shroud structures

叶冠结构	无喷气	有喷气
全冠	0.087242	0.091259
部分冠	0.529847	0.54178
尾缘切削优化冠	0.375742	0.398451
前尾缘均切削优化冠	0.427821	0.445154

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表 2 不同叶冠结构出口气流角对比

Table 2. Comparison of outlet airflow angles of different shroud structures

叶冠结构	无喷气	有喷气
全冠	1.3848815	1.0148148
部分冠	−12.01773	−12.03682
尾缘切削优化冠	−1.518056	−2.264189
前尾缘均切削优化冠	−7.527948	−7.570422

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表 3 不同叶冠结构出口总压损失系数对比

Table 3. Comparison of outlet total pressure loss coefficients of different shroud structures

叶冠结构	无喷气	有喷气
全冠	0.246974	0.216763
部分冠	0.25821	0.245612
尾缘切削优化冠	0.2571	0.196407
前尾缘均切削优化冠	0.267903	0.254286

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