蜂巢式双层壁冷却结构减阻优势研究

徐宁宁; 吕东; 孔星傲; 乐鑫灿; 王奉明

doi:10.13224/j.cnki.jasp.20230503

蜂巢式双层壁冷却结构减阻优势研究

doi: 10.13224/j.cnki.jasp.20230503

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.
中国航空发动机集团有限公司中国航空发动机研究院，北京 101304

基金项目: 中国航发先进航空动力创新工作站项目（HKCX2022-01-016）

详细信息

作者简介:
徐宁宁（1998-），女，硕士生，主要从事涡轮叶片冷却研究

通讯作者:
吕东（1979-），男，教授、博士生导师，博士，主要从事涡轮叶片冷却技术研究。E-mail：ld@dlut.edu.cn

中图分类号: V231.3
计量
- 文章访问数: 1056
- HTML浏览量: 250
- PDF量: 46
- 被引次数: 0
出版历程
- 收稿日期: 2023-08-01
- 网络出版日期: 2024-12-23

Study on advantages of flow resistance reduction for honeycomb-like double-wall cooling structures

1.
Innovation Lab of Gas Turbine Blade，School of Energy and Power Engineering，Dalian University of Technology，Dalian Liaoning 116024，China
2.
Aero Engine Academy of China，Aero Engine Corporation of China，Beijing 101304，China

摘要

摘要:
高冷效涡轮叶片需要采用双层壁冷却结构，但已有大量研究表明其冷气流动阻力过大，导致该类结构应用困难。为改善这一问题，一种蜂巢式双层壁冷却结构已经被提出。基于自研的小型风洞实验系统和3D打印制备的实验件，在常温常压工况下对两种双层壁结构进行了流阻对比实验。结果表明在相同的结构准则参数和来流雷诺数下，蜂巢式结构的总压损失比典型层板减少了20.5%～22.5%，总压恢复系数提高了最多1.4%；同时对实验过程进行了仿真复现，进一步明晰了该结构可有效组织气流和抑制多类旋涡的减阻机理。通过对实验结果的不确定性分析，以及实验与仿真结果的相互印证，表明了所得结论的可信性。
- 涡轮叶片 /
- 蜂巢式冷却 /
- 双层壁结构 /
- 流动阻力 /
- 风洞实验
Abstract:
Double-wall cooling structure should be applied to the high-cooling efficiency turbine blade. But the previous works discovered its tremendous flow resistance, which caused the difficulties in applications. A novel honeycomb-like double-wall cooling structure was proposed to solve this issue. Flow resistance comparison experiments between 2 double-wall structures were carried out using a small wind tunnel and 3D printing components under ordinary operating conditions. Compared with the typical lamilloy with the equal structural criterion numbers, the total pressure loss of the honeycomb-like scheme could be reduced by about 20.5% to 22.5% under the same upstream Reynolds number, and the total pressure recovery coefficient could be increased by up to 1.4%. The strengthening mechanism of the novel scheme was clearly revealed by replicating numerical simulations of the experimental process, with more effective flow organization and vorticity suppression. These advantages were proved by uncertainty analysis and verification between experiment and simulation methods.
- turbine blade /
- honeycomb-like cooling /
- double-wall structure /
- flow resistance /
- wind tunnel test

HTML

图 1 两模型计算域及边界条件

Figure 1. Domain and boundary conditions of 2 models

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图 2 计算域网格及局部加密

Figure 2. Mesh of domain and local refinements

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图 3 两算例的三维流线图

Figure 3. 3D streamlines of 2 results

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图 4 两算例流线沿程相对总压

Figure 4. Relative total pressure along streamlines of 2 results

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图 5 典型位置中截面相对总压分布

Figure 5. Relative total pressure distribution on middle section of typical locations

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图 6 两算例内的涡核

Figure 6. Vortex cores in 2 results

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图 7 两实验件结构图

Figure 7. Structural drawings of 2 test parts

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图 8 采用3D打印制作的两实验件

Figure 8. Two test parts made by 3D print

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图 9 实验台示意图

Figure 9. Layout of testbed

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图 10 $ \Delta p_{}^* $随Re的变化

Figure 10. Variation of $ \Delta p_{}^* $ with Re

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图 11 σ随Re的变化

Figure 11. Variation of σ with Re

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表 1 两模型主要结构参数

Table 1. Main structural parameters of 2 models

参数类型	参数名称	数值
有量纲	H₀/mm	6.00
	H₄/mm	6.00
	A_0s/mm²	106.42
	A_1s/mm²	2.07
	A_2s/mm²	40.62
	A_3s/mm²	2.07
无量纲	$ \gamma $	0.38
无量纲	$ \xi $	0.02

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表 2 网格无关性验证

Table 2. Grid independence verification

网格量/万	θ/%
53	29.36
95	12.96
248	3.37
596	−1.43

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表 3 湍流模型的结果相对误差θ

Table 3. Result relative deviation θ of turbulence models %

Re	θ
Re	k-ε模型	k-ω模型	SST模型
8450	−32.38	−7.88	−9.38
11299	−22.90	−4.92	−1.43
12653	−22.11	6.64	0.48
方均根	22.70	5.71	4.75

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表 4 边界条件及工质物性

Table 4. Boundary conditions and coolant physical properties

项目	参数	数值
项目	参数	典型工况	实验工况范围
进口	$ \dot m $/（kg/（s·m²））	1.77	0.47～2.13
进口	T₀/K	302.92	296.12～306.25
出口	p₄/kPa	102.89	102.81～103.01
出口	T₄/K	297.15	297.15
工质物性	μ/10⁻⁶ （kg/（m·s））	1.88	1.84～1.89
	ρ_spec/（kg/m³）	1.26	1.20～1.28
	λ/（W/（m·K））	0.026	0.026～0.027
	c_p/（kJ/（kg·K））	1.005	1.005

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表 5 典型位置中截面$ \overline {{\boldsymbol{p}}_{{\bf{s}}}^{\boldsymbol{*}}/{\boldsymbol{p}}_{{{\boldsymbol{0}} {\bf{s}}}}^{\boldsymbol{*}}} $

Table 5. $ \overline {{\boldsymbol{p}}_{{\bf{s}}}^{\boldsymbol{*}}/{\boldsymbol{p}}_{{{\boldsymbol{0}} {\bf{s}}}}^{\boldsymbol{*}}} $ on middle section of typical locations

结构类型	进气孔	夹层	气膜孔
典型层板结构	0.9986	0.9696	0.9595
蜂巢式结构	0.9979	0.9808	0.9700

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表 6 实验件结构参数

Table 6. Structure parameters of 2 test parts

结构类型	参数	数值
结构类型	参数	典型层板结构	蜂巢式结构
实验件整体	H₁/mm	1.26
	H₂/mm	1.31
	H₃/mm	1.90
	A₀/mm²	2128.34	2021.93
	A₃/mm²	41.43	39.41
	n/个	20	19
单元体	b/mm		0.93
	e/mm		2.53
	c/mm		0.83
	$ \delta $/mm		0.93
	L/mm	10.32	6.40
	ϕd₁/mm	1.62
	ϕd₂/mm	3.60	5.09
	ϕd₃/mm	1.62
	α/（°）	90	35
	β/（°）	35

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