高压涡轮叶片冷却方案优化改进

骆剑霞; 陈大为; 谭智勇

doi:10.13224/j.cnki.jasp.20240781

高压涡轮叶片冷却方案优化改进

doi: 10.13224/j.cnki.jasp.20240781

中国航发商用航空发动机有限责任公司，上海 200241

详细信息

作者简介:
骆剑霞（1987-），女，高级工程师，博士，研究领域为涡轮叶片冷却结构设计。E-mail：luoluojianxia@163.com

中图分类号: V232.4
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出版历程
- 收稿日期: 2024-11-18
- 网络出版日期: 2026-05-16

Optimization and improvement of the cooling scheme for high pressure turbine blade

Commercial Aircraft Engine Company Limited，Aero Engine Corporation of China，Shanghai 200241，China

摘要

摘要:
为了提高冷却效果，开展了转子叶片冷却方案的优化设计，并验证了叶片综合冷效。对于原型叶片，叶片前缘与尾缘为高温区，吸力面中部温度也比较高。随着流量比的增大，压力面与吸力面分别在7%和5%以上工况出现了气膜覆盖效果变差导致测点温度升高的情况。优化方案叶片通过内腔与气膜孔设计优化，实现了叶身温度均匀性与整体冷效的同步提升。在相同的流量比下，优化方案压力面与吸力面前部区域测点温度最大降幅约30 K，使得整体综合冷效提高0.02。随着流量比的增大，优化方案的气膜一直能提供很好的覆盖效果，叶身测点温度持续降低，综合冷效从0.568逐渐增加至0.613。
- 高压涡轮 /
- 叶片 /
- 冷却方案 /
- 流量比 /
- 综合冷效
Abstract:
To enhance the cooling effect, an optimized cooling scheme for the rotor blade was developed, and overall cooling effectiveness of the blade was verified. For the prototype blade, elevated temperatures were observed at the leading edge, the trailing edge, and the mid-region of the suction side.. As the flow ratio increased to 5% and 7%, the film cooling effectiveness deteriorated on both the pressure and suction sides. This degradation led to a corresponding temperature rise at the measured points. The optimized blade design achieved a more uniform blade temperature distribution and enhanced overall cooling efficiency through optimization of the internal cavity and film hole design. At the same flow ratio, temperatures at the measurement points in the front regions of the pressure and suction sides dropped by about 30K compared to the prototype design, with an improvement of 0.02 in overall cooling effectiveness. As the flow ration increased, the optimized design consistently provided good film coverage, leading to a continuous decrease in blade measurement point temperatures with the overall cooling effectiveness increasing from 0.568 to 0.613.
- high pressure turbine /
- blade /
- cooling scheme /
- flow ratio /
- overall cooling effectiveness

HTML

图 1 试验设备示意图

Figure 1. Illustration of the test system

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图 2 冷效试验段示意图

Figure 2. Cooling effectiveness testing section schematic diagram

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图 3 原型叶片冷却结构与测点示意图

Figure 3. Prototype blade cooling structure and measurement points

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图 4 不同冷气流量比下原型叶片表面温度分布

Figure 4. Surface temperature distribution of the prototype blade at various cooing flow ratios

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图 5 原型与优化叶片叶身中截面测点温度对比

Figure 5. Mid-Span section measuring point temperature comparison between prototype and optimized blades

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图 6 优化叶片冷却结构与测点示意图

Figure 6. Optimized blade cooling structure and measurement points

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图 7 不同冷气流量比下优化叶片表面温度分布

Figure 7. Optimized blade surface temperature distribution at various cooling flow ratios

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图 8 原型与优化叶片综合冷效对比

Figure 8. Overall cooling effectiveness of the prototype and optimized blade

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表 1 各排气膜孔与劈缝出流占总流量比例

Table 1. Flow rate from each film hole and slot to total cooling flow

位置	冷气流量比/%
位置	原型叶片	优化设计
气膜孔1	8.33	7.34
气膜孔2	6.04	5.79
气膜孔3	4.95	5.21
气膜孔4	4.66	4.83
气膜孔5	4.21	4.83
气膜孔6	4.25	4.83
气膜孔7	3.49	4.25
气膜孔8	2.54	4.83
气膜孔9	3.53	3.47
气膜孔10	2.74	2.90
气膜孔11		1.74
劈缝	40.77	33.40

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