基于型面偏差的涡轮叶片气膜孔位置自适应优化与冷效验证研究

廖玉婷; 刘松; 高杰; 董一巍; 张霄昕; 郭文

doi:10.13224/j.cnki.jasp.20250567

基于型面偏差的涡轮叶片气膜孔位置自适应优化与冷效验证研究

doi: 10.13224/j.cnki.jasp.20250567

廖玉婷^{1, 2,},
刘松^{2, 3},
高杰²,
董一巍^1,*, ,,
张霄昕¹,
郭文²

1.
厦门大学航空航天学院，厦门 361100
2.
中国航发四川燃气涡轮研究院，成都 610500
3.
北京航空航天大学航空发动机研究院，北京 101304

基金项目: 国家自然科学基金（52475491，51705440）；慧眼行动（A0DC5030）；航空科学基金（20170368001，20230003068002，20240003068001）；四川省科技计划项目（2025YFHZ0039, 2026YFHZ0284）

详细信息

作者简介:
廖玉婷（2001-），女，硕士生，主要从事涡轮叶片冷却方面的研究。E-mail：34720231151559@stu.xmu.edu.cn

通讯作者:
董一巍（1982-），男，副教授，博士，主要从事叶片测量制造、冷却方面的研究。E-mail：yiweidong@xmu.edu.cn

中图分类号: V232.4
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出版历程
- 收稿日期: 2025-12-04
- 网络出版日期: 2026-05-11

Adaptive position optimization of film cooling holes and cooling effectiveness verification based on turbine blade profile deviation

Liao Yuting^{1, 2
,},
Liu Song^{2, 3},
Gao Jie²,
Dong Yiwei^{1,*
, ,},
Zhang Xiaoxin¹,
Guo Wen²

1.
School of Power and Energy，Xiamen University，Xiamen 361100，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China
3.
Research Institute of Aero-Engine，Beihang University，Beijing 101304，China

摘要

摘要:
涡轮叶片在成形过程中易产生型面偏差，若气膜孔仍依据理想设计叶型进行加工，将导致孔位相对实际型面漂移并削弱气膜冷却性能。提出一种基于实测型面偏差的气膜孔位置自适应优化方法。在点云测量与逆向建模基础上获得包含真实型面偏差的叶片模型，构建刚体变换求解的孔位自适应优化，建立考虑型面偏差的优化叶片，并建立共轭传热数值模型和冷效试验方案，对设计叶片、按设计孔位加工的逆向叶片以及优化叶片在多工况下的冷却性能进行对比。典型工况下，A2叶片中截面20个测点的计算与试验结果表明：最大温差为33.9 K，温度平均偏差约为1.95%，模型具有较好可靠性；相对于仅考虑型面偏差而未调整孔位的叶片，自适应优化叶片在叶盆两排气膜孔附近4个敏感测点的仿真结果中平均温降分别为9.82、7.72、2.61 K 和 2.82 K，中截面平均冷却效率提高约1.3%，在低温高流量冷气工况下优势更为明显。研究结果表明：气膜孔自适应优化方法能够减弱孔位漂移对气膜覆盖和局部温度峰值的不利影响，为涡轮叶片在制造偏差条件下的冷却结构优化设计提供技术支撑。
- 涡轮叶片 /
- 型面偏差 /
- 气膜孔重定位 /
- 点云测量 /
- 逆向建模 /
- 冷却效率试验 /
- CFD数值仿真
Abstract:
Manufacturing deviations in turbine blades inevitably cause film cooling hole misalignment relative to the cast profile, compromising cooling effectiveness. This study proposed an adaptive hole positioning optimization method based on 3D-scanned geometric deviations, and validated through conjugate heat transfer (CHT) simulations and experiments. By integrating reverse engineering with a rigid-body transformation algorithm, an optimized blade model was generated to compensate for profile distortions. Comparative analysis against the ideal design and an unadjusted reverse-engineered blade demonstrated that the proposed method significantly mitigated the adverse effects of hole drift. Under typical operating conditions, the optimized blade achieved local temperature reductions of up to 9.82 K in critical pressure-side regions and improved mid-span cooling efficiency by approximately 1.3%, particularly at high coolant mass flow rates. These findings confirm the efficacy of the adaptive strategy in enhancing cooling robustness under real-world manufacturing constraints.
- turbine blade /
- profile deviation /
- film cooling hole repositioning /
- point cloud measurement /
- reverse modeling /
- experimental validation /
- CFD simulation

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图 1 A1叶片流体域及固体域模型

Figure 1. A1 blade fluid and solid domain model

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图 2 计算域网格示意图

Figure 2. Schematic diagram of the computational mesh

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图 3 A2叶片的网格无关性分析

Figure 3. Mesh independence analysis of the A2 blade

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图 4 A2叶片1838万网格下的表面Y⁺值

Figure 4. Surface Y⁺ value for A2 blade at 18.38 million meshes

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图 5 对加工后的涡轮叶片进行逆向建模

Figure 5. Reverse modeling method for machined turbine blades

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图 6 设计轮廓与实际叶片轮廓上气膜孔位置的改变

Figure 6. Change in film cooling hole positions on the design and actual profiles

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图 7 涡轮叶片变形示意图

Figure 7. Diagram of turbo blade deformation

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图 8 冷效试验原理图

Figure 8. Cold efficiency test schematic

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图 9 试验流程图

Figure 9. Experimental flowchart

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图 10 叶片装夹在转接段叶栅内

Figure 10. Blade is clamped inside the transition section blade sleeve

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图 11 转接段结构实物图

Figure 11. Physical diagram of adapter segment structure

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图 12 不同工况下20个测点温度变化曲线

Figure 12. Temperature variation curves for 20 measurement points under different operating conditions

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图 13 热电偶位置布置示意图

Figure 13. Schematic diagram of thermocouple position arrangement

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图 14 加工后试验叶片与3D模型的体偏差对比图

Figure 14. Comparison diagram of dimensional deviations between machined test blades and 3D models

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图 15 A2涡轮叶片中截面测点仿真与试验结果对比

Figure 15. Comparison of simulation and experimental results at the cross-section measurement points of A2 turbine blade

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图 16 不同工况下叶盆气膜孔附近测点温度变化曲线

Figure 16. Temperature variation curves at measuring points near the blade-bowl gas film holes under different operating conditions

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图 17 优化后A3叶片表面测点温降变化曲线

Figure 17. Optimised A3 blade surface measurement point temperature drop variation curve

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图 18 不同工况条件下A3表面测点温降变化曲线

Figure 18. Temperature drop variation curve of A3 surface measurement points under different operating conditions

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图 19 3个叶片在设计点工况下的温度云图

Figure 19. Temperature contour of three blades under design point conditions

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表 1 DD6导热系数

Table 1. DD6 thermal conductivity

温度/K	导热系数/（W/（m·K））
293	6.70
373	8.00
473	9.45
573	11.15
673	13.40
773	15.35
873	17.60
973	20.20
1073	22.30
1173	24.55
1273	26.80
1373	28.95
1473	30.90
1573	33.20

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表 2 叶片流量试验及重复性试验数据

Table 2. Blade flow test and repeatability test data

叶片编号	试验次数	进口压比	叶片流量/（g/s）	偏差/%
A1	第1次	2.0	7.68
	第1次	3.0	11.91
	第2次	2.0	7.66	−0.28
	第2次	3.0	11.90	−0.07
A2	第1次	2.0	8.17
	第1次	3.0	12.69
	第2次	2.0	8.22	0.65
	第2次	3.0	12.74	0.42
A3	第1次	2.0	7.95
	第1次	3.0	12.40
	第2次	2.00	7.92	−0.33
	第2次	3.00	12.35	−0.47

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表 3 工况表

Table 3. Operating conditions table

工况	进口温度/K	进口总压/kPa	出口静压/kPa	冷气温度/K	冷气流量/ （kg/s）
1	973	800	518.5	537.4	0.0229
2	973	800	518.5	511.6	0.0229
3	973	800	518.5	487.0	0.0229
4	973	800	518.5	465.1	0.0229
5	973	800	518.5	447.6	0.0229
6	973	800	567.7	537.4	0.0229
7	973	800	473.1	537.4	0.0229
8	973	800	421.3	537.4	0.0229
9	973	800	380.1	537.4	0.0229
10	973	800	518.5	537.4	0.0257
11	973	800	518.5	537.4	0.0206
12	973	800	518.5	537.4	0.0195
13	973	800	518.5	537.4	0.0161
14	973	800	518.5	537.4	0.0126

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