基于双层壁冷却结构的综合冷效数值解耦研究

刘润洲; 李海旺; 由儒全; 黄毅; 陶智

doi:10.13224/j.cnki.jasp.20220372

基于双层壁冷却结构的综合冷效数值解耦研究

doi: 10.13224/j.cnki.jasp.20220372

刘润洲^{1, 3,},
李海旺^{1, 3},
由儒全^{1, 3,*, ,},
黄毅^{1, 3},
陶智^{1, 2, 3}

1.
北京航空航天大学航空发动机研究院，北京 102206
2.
北京航空航天大学能源与动力工程学院，北京 102206
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 102206

基金项目: 国家科技重大专项（2017-Ⅲ-0010-0036）；北京市自然科学基金（3222034）；先进航空动力创新工作站项目（HKCX2022-01-007）

详细信息

作者简介:
刘润洲（1997-），男，博士生，主要从事涡轮叶片冷却研究。E-mail：liurunzhou_buaa@163.com

通讯作者:
由儒全（1991-），男，副研究员，博士，主要从事涡轮叶片冷却研究。E-mail：youruquan10353@buaa.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2022-05-25
- 网络出版日期: 2023-10-19

Numerical decoupling of overall cooling effectiveness based on double-wall cooling structure

LIU Runzhou^{1, 3
,},
LI Haiwang^{1, 3},
YOU Ruquan^{1, 3,*
, ,},
HUANG Yi^{1, 3},
TAO Zhi^{1, 2, 3}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 102206，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics， Beihang University，Beijing 102206，China

摘要

摘要:
采用数值解耦的方法，定量分析了双层壁平板冷却结构的综合冷效与内部冷却、气膜孔内冷却和冷气覆盖之间的关系。吹风比为0.25、0.5、1和1.5。通过研究发现，吹风比对双层壁模型的综合冷效有明显影响。当吹风比由0.25增大到1.5时，综合冷效增大57.9%。内部冷却占主导地位的区域主要是冲击气流的驻点区。气膜孔内冷却影响最大的区域为气膜孔出口的上游，而且沿流向孔内冷却的影响逐渐减小。冷气覆盖对综合冷效的影响沿流向逐渐积累，在第3个气膜孔出口附近冷气覆盖的影响最大。而且在冷气覆盖区域的影响要大于在远离气膜孔区域的影响。当吹风比增大至1时，孔内冷却对综合冷效的影响已经超过了冷气覆盖。
- 综合冷效 /
- 气膜冷却 /
- 内部冷却 /
- 解耦 /
- 吹风比 /
- 平板模型
Abstract:
Numerical decoupling method was used to quantitatively analyze the relationship between the overall cooling effectiveness of impingement-effusion model and the internal cooling, bore cooling and coolant coverage. The blowing ratios were 0.25, 0.5, 1 and 1.5. It was found that the blowing ratio had a significant effect on the comprehensive cooling effect of the impact divergence model. When the blowing ratio increased from 0.25 to 1.5, the overall cooling effectiveness increased by 57.9%. The stagnation region of impingement jet was mainly dominated by internal cooling. The region where the bore cooling had the greatest influence on the overall cooling effectiveness was located upstream of the film hole outlet, and the influence of bore cooling along the streamwise direction was gradually reduced. The influence of coolant coverage on the overall cooling effectiveness gradually accumulated along the streamwise direction, and the influence near the third film hole outlet was the largest. The influence in the downstream of film hole was greater than that in the region away from the film hole. When the blowing ratio increased to 1, the effect of bore cooling on the overall cooling effectiveness exceeded that of coolant coverage.
- overall cooling effectiveness /
- film cooling /
- internal cooling /
- decoupling method /
- blowing ratio /
- flat-plate model

HTML

图 1 仿真模型示意图

Figure 1. Schematic diagram of simulation model

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图 2 不同模型的边界条件

Figure 2. Boundary conditions for different cases

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图 3 仿真模型的边界条件设置

Figure 3. Boundary conditions of simulation model

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图 4 数值仿真结果与实验结果的对比

Figure 4. Comparison of numerical simulation and experimental results

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图 5 网格无关性验证

Figure 5. Grid independence verification

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图 6 综合冷效云图

Figure 6. Contours of overall cooling effectiveness

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图 7 绝热冷效云图

Figure 7. Contours of adiabatic film cooling effectiveness

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图 8 M=0.5时y/D=2.5处无量纲温度分布（无内部冷却）

Figure 8. Distribution of dimensionless temperature at slice y/D=2.5 for case without internal cooling with M=0.5

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图 9 综合冷效差值Δϕ（无内部冷却）

Figure 9. Δϕ between base case and case without internal cooling

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图 10 M=0.5时y/D=2.5处无量纲温度分布（无孔内冷却）

Figure 10. Distribution of dimensionless temperature at slice y/D=2.5 for case without bore cooling with M=0.5

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图 11 综合冷效差值Δϕ（无孔内冷却）

Figure 11. Δϕ between base case and case without bore cooling

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图 12 吹风比M=0.5时y/D=2.5处速度分布

Figure 12. Distribution of velocity at slice y/D=2.5 for case without coolant coverage with M=0.5

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图 13 综合冷效差值Δϕ（无冷气覆盖）

Figure 13. Δϕ between base case and case without coolant coverage

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图 14 近壁温度分布

Figure 14. Fluid temperature near the wall

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图 15 综合冷效的展向平均结果

Figure 15. Laterally-averaged overall cooling effectiveness for different cases

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表 1 边界条件设置

Table 1. Boundary conditions

参数数值

T_g/K 600
T_c/K 303
T_g/T_c 1.98
Re_g 3300
M 0.25, 0.5, 1, 1.5
k_solid/（W/（m·K）） 10.6

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表 2 面积平均综合冷效结果

Table 2. Area-averaged overall cooling effectiveness

吹风比面积平均综合冷效

0.25 0.3441
0.5 0.4491
1 0.5187
1.5 0.5434

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参考文献(28)

[1]	SEN B,SCHMIDT D L,BOGARD D G. Film cooling with compound angle holes: heat transfer[J]. Journal of Turbomachinery,1996,118(4): 800-806. doi: 10.1115/1.2840937
[2]	ZHANG Jingzhou,ZHANG Shengchang,WANG Chunhua,et al. Recent advances in film cooling enhancement: a review[J]. Chinese Journal of Aeronautics,2020,33(4): 1119-1136. doi: 10.1016/j.cja.2019.12.023
[3]	ACHARYA S, KANANI Y. Advances in film cooling heat transfer[M]//Advances in Heat Transfer. Amsterdam, Holland: Elsevier, 2017: 91-156.
[4]	BOGARD D G,THOLE K A. Gas turbine film cooling[J]. Journal of Propulsion and Power,2006,22(2): 249-270. doi: 10.2514/1.18034
[5]	HAN J C. Turbine blade cooling studies at Texas A&M University: 1980-2004[J]. Journal of Thermophysics and Heat Transfer,2006,20(2): 161-187. doi: 10.2514/1.15403
[6]	GRITSCH M,COLBAN W,SCHÄR H,et al. Effect of hole geometry on the thermal performance of fan-shaped film cooling holes[J]. Journal of Turbomachinery,2005,127(4): 718-725. doi: 10.1115/1.2019315
[7]	GRITSCH M,SCHULZ A,WITTIG S. Adiabatic wall effectiveness measurements of film-cooling holes with expanded exits[J]. Journal of Turbomachinery,1998,120(3): 549-556. doi: 10.1115/1.2841752
[8]	SAUMWEBER C,SCHULZ A. Free-stream effects on the cooling performance of cylindrical and fan-shaped cooling holes[J]. Journal of Turbomachinery,2012,134(6): 061007.1-061007.12.
[9]	SAUMWEBER C,SCHULZ A. Effect of geometry variations on the cooling performance of fan-shaped cooling holes[J]. Journal of Turbomachinery,2012,134(6): 061008.1-061008.16.
[10]	BRYANT C E,RUTLEDGE J L. A computational technique to evaluate the relative influence of internal and external cooling on overall effectiveness[J]. Journal of Turbomachinery,2020,142(5): 051008.1-051008.11.
[11]	ALBERT J E, BOGARD D G, CUNHA F. Adiabatic and overall effectiveness for a film cooled blade[R]. ASME Paper GT2004-53998, 2004.
[12]	CHAVEZ K, SLAVENS T N, BOGARD D. Effects of internal and film cooling on the overall effectiveness of a fully cooled turbine airfoil with shaped holes[R]. ASME Paper GT2016-57992, 2016.
[13]	NATHAN M L,DYSON T E,BOGARD D G,et al. Adiabatic and overall effectiveness for the showerhead film cooling of a turbine vane[J]. Journal of Turbomachinery,2014,136(3): 031005.1-031005.9.
[14]	RAVELLI S, DOBROWOLSKI L, BOGARD D G. Evaluating the effects of internal impingement cooling on a film cooled turbine blade leading edge[R]. ASME Paper GT2010-23002, 2010.
[15]	LIU Cunliang,XIE Gang,WANG Rui,et al. Study on analogy principle of overall cooling effectiveness for composite cooling structures with impingement and effusion[J]. International Journal of Heat and Mass Transfer,2018,127: 639-650. doi: 10.1016/j.ijheatmasstransfer.2018.07.085
[16]	XIE G, LIU C L, WANG R, et al. Experimental study on analogy principle of overall cooling effectiveness for composite cooling structures with both internal cooling and film cooling[R]. ASME Paper GT2019-90705, 2019.
[17]	MENSCH A,THOLE K A. Overall effectiveness of a blade endwall with jet impingement and film cooling[J]. Journal of Engineering for Gas Turbines and Power,2014,136(3): 031901.1-031901.13.
[18]	MENSCH A,THOLE K A,CRAVEN B A. Conjugate heat transfer measurements and predictions of a blade endwall with a thermal barrier coating[J]. Journal of Turbomachinery,2014,136(12): 121003.1-121003.11.
[19]	MENSCH A,THOLE K A. Conjugate heat transfer analysis of the effects of impingement channel height for a turbine blade endwall[J]. International Journal of Heat and Mass Transfer,2015,82: 66-77. doi: 10.1016/j.ijheatmasstransfer.2014.10.076
[20]	TERRELL E J, MOUZON B D, BOGARD D G. Convective heat transfer through film cooling holes of a gas turbine blade leading edge[R]. ASME Paper GT2005-69003, 2005.
[21]	MOUZON B D, TERRELL E J, ALBERT J E, et al. Net heat flux reduction and overall effectiveness for a turbine blade leading edge[R]. ASME Paper GT2005-69002, 2005.
[22]	RAVELLI S,BARIGOZZI G. Numerical evaluation of heat/mass transfer analogy for leading edge showerhead film cooling on a first-stage vane[J]. International Journal of Heat and Mass Transfer,2019,129: 842-854. doi: 10.1016/j.ijheatmasstransfer.2018.10.034
[23]	BRYANT C E,WIESE C J,RUTLEDGE J L,et al. Experimental evaluations of the relative contributions to overall effectiveness in turbine blade leading edge cooling[J]. Journal of Turbomachinery,2019,141(4): 041007.1-041007.15.
[24]	XIE Gang,LIU Cunliang,NIU Jiajia,et al. Experimental investigation on analogy principle of conjugate heat transfer for effusion/impingement cooling[J]. International Journal of Heat and Mass Transfer,2020,147: 118919.1-118919.13.
[25]	SHI B, LI J, LI M F, et al. Overall cooling effectiveness on a flat plate with both film cooling and impingement cooling in hot gas condition ASME Paper[R]. ASME Paper GT2016-57224, 2016.
[26]	GOMATAM RAMACHANDRAN S,SHIH T I P. Biot number analogy for design of experiments in turbine cooling[J]. Journal of Turbomachinery,2015,137(6): 061002.1-061002.14.
[27]	ZHOU Weilun, DENG Qinghua, FENG Zhenping. Conjugate heat transfer analysis for laminated cooling effectiveness: Part A effects of surface curvature[R]. ASME Paper GT2016-57243, 2016.
[28]	DENG Qinghua, ZHOU Weilun, FENG Zhenping. Conjugate heat transfer analysis for laminated cooling effectiveness: Part B effects of film hole incline angle[R]. ASME Paper GT2016-57256, 2016.