收缩型双射流孔气膜冷却特性与损失机理

康忠; 李国庆; 张深; 王晓东; 张燕峰; 卢新根

doi:10.13224/j.cnki.jasp.20210202

收缩型双射流孔气膜冷却特性与损失机理

doi: 10.13224/j.cnki.jasp.20210202

康忠^{1, 2},
李国庆^{1, 3,*, ,},
张深^{1, 3},
王晓东²,
张燕峰^{1, 3},
卢新根^{1, 3}

1.
中国科学院工程热物理研究所轻型动力重点实验室，北京 100190
2.
华北电力大学能源动力与机械工程学院，北京 102206
3.
中国科学院大学航空宇航学院，北京 100049

基金项目: 国家自然科学基金（51976214）

详细信息

作者简介:
康忠（1995-），男，硕士生，主要从事涡轮叶片气膜冷却研究

通讯作者:
李国庆（1981-），男，研究员，博士，主要从事航空发动机气动与传热研究。E-mail：liguoqing@iet.cn

中图分类号: V231.1
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- 文章访问数: 310
- HTML浏览量: 54
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- 被引次数: 0
出版历程
- 收稿日期: 2021-04-28
- 网络出版日期: 2022-12-21

Film cooling characteristics and loss mechanism of contracted double-jet hole

KANG Zhong^{1, 2},
LI Guoqing^{1, 3,*
, ,},
ZHANG Shen^{1, 3},
WANG Xiaodong²,
ZHANG Yanfeng^{1, 3},
LU Xingen^{1, 3}

1.
Laboratory of Light-duty Gas-turbine，Institute of Engineering Thermophysics， Chinese Academy of Sciences，Beijing 100190，China
2.
School of Energy，Power and Mechanical Engineering，North China Electric Power University，Beijing 102206，China
3.
School of Aeronautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China

摘要

摘要:
在兼顾气膜冷却效率的条件下，为了降低气膜冷却带来的气动损失，采用数值模拟的方法研究了双射流孔和收缩型双射流孔的气膜冷却特性。对比分析了不同吹风比（0.5～2.0）工况下气膜冷却效率和损失分布规律。结果表明：当吹风比高于1.0时，收缩型双射流孔促进冷气横向发展，冷却效率提高；当吹风比增加到2.0时，收缩型双射流孔可以防止冷气吹离壁面。与双射流孔相比，收缩型双射流孔入口冷气均匀加速，消除了孔内低速区造成的堵塞，流场趋于均匀，孔内损失明显降低，从而整体上降低了气膜冷却引起的总压损失。
- 气膜冷却 /
- 气膜冷却效率 /
- 总压损失 /
- 气膜孔 /
- 损失机理
Abstract:
Film cooling characteristics and loss mechanism of double-jet hole and contracted double-jet hole with blowing ratio varying from 0.5 to 2.0 were numerically simulated. Results showed that the lateral film coverage developed and the film cooling effectiveness was promoted for the Contracted Double-jet hole when the blowing ratio was bigger than 1.0. When the blowing ratio reached 2.0, the Contracted Double-jet hole can prevent the film lift-off. Compared with the Double-jet hole, the cooling flow at the inlet of the Contracted Double-jet hole was accelerated evenly and the blockage caused by the low velocity zone in the hole was eliminated so that the flow field became uniform and the total pressure loss was reduced.
- film cooling /
- film cooling effectiveness /
- total pressure loss /
- film cooling hole /
- loss mechanism

HTML

图 1 计算域模型

Figure 1. Computational domain model

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图 2 气膜孔结构示意图

Figure 2. Schematic of film cooling configuration

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图 3 数值模拟网格

Figure 3. Numerical simulation grids

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图 4 实验与数值模拟结果对比

Figure 4. Comparison between numerical and experimental result

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图 5 网格无关性验证

Figure 5. Grid independence study

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图 6 横向平均气膜冷却效率

Figure 6. Laterally averaged film cooling effectiveness

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图 7 反肾型涡对理想形状

Figure 7. Idealized shape of the anti-kidney vortex pair

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图 8 DJFC与DJFC7绝热气膜冷却效率分布

Figure 8. Adiabatic film cooling effectiveness distribution for DJFC and DJFC7

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图 9 X/D截面总温分布与二次流（M=1.0）

Figure 9. Total temperature distribution and secondary flow at X/D plane （M=1.0）

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图 10 DJFC与DJFC7总压损失系数对比

Figure 10. Comparison of the total pressure loss coefficient of DJFC and DJFC7

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图 11 DJFC和DJFC7的$\zeta_{p,{\rm{hole}}}$和$\zeta_{p,{\rm{mix}}}$对比

Figure 11. Comparison of $\zeta_{p,{\rm{hole}}}$ and $\zeta_{p,{\rm{mix}}}$ of DJFC and DJFC7

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图 12 气膜孔中心面马赫数与矢量云图

Figure 12. Calculated Mach number distribution with flow vectors at center plane of film cooling holes

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表 1 边界条件设置

Table 1. Boundary conditions

边界条件设计值

冷气入口总温 T_tc/K 290
主流入口总压 p_tg/kPa 128
主流入口马赫数 Ma 0.6
主流出口静压 p_out/kPa 96
总温比 T_tc/T_tg 0.54
密度比 ρ_c/ρ_g 1.8
吹风比 M 0.5～2.0

下载: 导出CSV

表 2 Hole1与Hole2吹风比

Table 2. Calculated blowing ratios of Hole1 and Hole2

模型 M Hole1 Hole2 M_av

DJFC 0.5 0.548 0.428 0.488
1.0 0.992 0.966 0.979
1.5 1.473 1.485 1.479
2.0 1.977 1.981 1.979
DJFC7 0.5 0.594 0.386 0.490
1.0 1.017 0.953 0.985
1.5 1.501 1.457 1.479
2.0 1.993 1.963 1.978

下载: 导出CSV

参考文献(24)

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收缩型双射流孔气膜冷却特性与损失机理

doi: 10.13224/j.cnki.jasp.20210202

作者简介:
康忠（1995-），男，硕士生，主要从事涡轮叶片气膜冷却研究

通讯作者:
李国庆（1981-），男，研究员，博士，主要从事航空发动机气动与传热研究。E-mail：liguoqing@iet.cn

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Film cooling characteristics and loss mechanism of contracted double-jet hole

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目录

边界条件	设计值
冷气入口总温 T_tc/K	290
主流入口总压 p_tg/kPa	128
主流入口马赫数 Ma	0.6
主流出口静压 p_out/kPa	96
总温比 T_tc/T_tg	0.54
密度比 ρ_c/ρ_g	1.8
吹风比 M	0.5～2.0

模型	M	Hole1	Hole2	M_av
DJFC	0.5	0.548	0.428	0.488
	1.0	0.992	0.966	0.979
	1.5	1.473	1.485	1.479
	2.0	1.977	1.981	1.979
DJFC7	0.5	0.594	0.386	0.490
	1.0	1.017	0.953	0.985
	1.5	1.501	1.457	1.479
	2.0	1.993	1.963	1.978

留言板

收缩型双射流孔气膜冷却特性与损失机理

doi: 10.13224/j.cnki.jasp.20210202

作者简介: 康忠（1995-），男，硕士生，主要从事涡轮叶片气膜冷却研究

通讯作者: 李国庆（1981-），男，研究员，博士，主要从事航空发动机气动与传热研究。E-mail：liguoqing@iet.cn

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出版历程

Film cooling characteristics and loss mechanism of contracted double-jet hole

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出版历程

目录

作者简介:
康忠（1995-），男，硕士生，主要从事涡轮叶片气膜冷却研究

通讯作者:
李国庆（1981-），男，研究员，博士，主要从事航空发动机气动与传热研究。E-mail：liguoqing@iet.cn