基于阵列式陶瓷基复合材料铠甲的涡轮叶片冷却方案

吕东; 戴小钦; 刘英实; 孔星傲; 李泳凡

doi:10.13224/j.cnki.jasp.20240525

基于阵列式陶瓷基复合材料铠甲的涡轮叶片冷却方案

doi: 10.13224/j.cnki.jasp.20240525

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: HY行动项目（KZ38230132）

详细信息

作者简介:
吕东（1979-），男，教授、博士生导师，博士，主要从事涡轮叶片冷却方面的研究。E-mail：ld@dlut.edu.cn

中图分类号: V232
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- 被引次数: 0
出版历程
- 收稿日期: 2024-07-30
- 网络出版日期: 2024-11-19

Turbine blade cooling scheme based on arrayed ceramic matrix composite armors

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:
基于金属与非金属材料组合式结构的设计思想，设计了一种采用阵列式陶瓷基复合材料（CMC）铠甲的涡轮叶片冷却方案。通过在叶片前部高热负荷区覆盖铠甲并代替原有叶型，以及在其间隙中通少量冷却气的方式，来加强对叶片金属基体的热防护。采用了三维流热耦合数值仿真方法，以及与典型气膜冷却对比的方式，对方案的强化冷却机理和可达到的效果开展了研究，并对部分设计方法进行了总结。方案在冷气用量降低了24.2%的同时，还可将金属区域冷却效果大幅度提高69.2%，达到了0.95，热防护效果显著。而此时CMC铠甲仍有不低于130 K的温度裕度，表明燃气温度在2000 K基础上还可以进一步提高。在设计方法和原则上，为避免出现前缘燃气入侵，应保证冷气压比不低于1.03。可通过使铠甲间缝隙交错和倾斜的优化方式来加强冷却效果。
- 涡轮叶片 /
- 陶瓷基复合材料 /
- 阵列式铠甲 /
- 气膜冷却 /
- 燃气入侵 /
- 温度裕度
Abstract:
Based on the design philosophy of assembly between metal and non-metal materials, a turbine blade cooling scheme which applied arrayed ceramic matrix composite (CMC) armors was designed. These armors replaced the airfoil, and covered the high thermal load regions at the front part of the blade. And a few coolants were injected through the gaps between them, thus a well thermal protection to the metal substrate was achieved. A three-dimensional flow and thermal coupled numerical simulation method was employed, along with the comparison with a typical film cooling. The cooling enhanced mechanisms and attainable effects of this scheme were revealed, and some design criteria and methods were summarized. The novel scheme reduced the coolant mass flow rate by 24.2%, while improving the metal region cooling efficiency by 69.2%, up to a number of 0.95. Meanwhile, the temperature margin of the CMC armors was still above 130 K, which indicated the potential for further increasing the gas temperature beyond 2000 K. In terms of design principles, the pressure ratio of coolant should be no less than 1.03 to prevent gas intrusion at the leading edge. The cooling efficiency can be enhanced by optimizing the interlaced and inclined arrangements of the gaps between the CMC armors.
- turbine blade /
- ceramic matrix composite /
- arrayed armors /
- film cooling /
- gas intrusion /
- temperature margin

HTML

图 1 基于阵列式CMC铠甲的冷却方案

Figure 1. Cooling scheme based on arrayed CMC armors

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图 2 冷气流动路径示意图

Figure 2. Diagram of coolant flow path

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图 3 气膜冷却仿真模型

Figure 3. Simulation model of film cooling

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图 4 网格及局部加密

Figure 4. Mesh and local refinements

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图 5 θ随π变化

Figure 5. Variation of θ with π

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图 6 冷气三维流线图（π=1.03）

Figure 6. 3D streamlines of coolant （π=1.03）

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图 7 CMC铠甲方案燃气流线及β云图（π=1.03）

Figure 7. Gas streamlines and β contours of CMC armors scheme （π=1.03）

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图 8 两种方案金属区域T_w云图（π=1.03）

Figure 8. Metal region T_w contours of both schemes （π=1.03）

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图 9 η随θ的变化

Figure 9. Variation of η with θ

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图 10 CMC铠甲T_w云图（π=1.03）

Figure 10. T_w contours of CMC armors （π=1.03）

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图 11 前缘铠甲T_w云图和各π工况下的φ

Figure 11. T_w contours of leading edge armors and φ of each π condition

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表 1 边界条件及工质物性

Table 1. Boundary conditions & material characteristics

位置	参数	数值
燃气进口	总压$p_{\mathrm{g}}^* $/kPa	2026.5
	总温$T_{\mathrm{g}}^* $/K	2000
	湍流度I_g/%	10.0
冷气进口	总压$p_{\mathrm{c}}^* $/kPa	（1.01～1.05）$p_{\mathrm{g}}^* $
	静温T_c/K	700
	湍流度I_c/%	5.0
出口	静压p_out/kPa	1114.6
主要物性	金属导热系数λ_m/（W/（m·K））		20.0
主要物性	CMC导热系数λ_cmc/（W/（m·K））		8.0

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