NACA0021和NACA4822翼型肋通道中环境空气流动传热特性的实验研究

李勇; 张迎春; 付虞; 周棋润; 赵雨菲; 杨森杰; 马素霞

doi:10.21656/1000-0887.440331

NACA0021和NACA4822翼型肋通道中环境空气流动传热特性的实验研究

doi: 10.21656/1000-0887.440331

李勇^{1, 2, ,},
张迎春³,
付虞¹,
周棋润¹,
赵雨菲¹,
杨森杰¹,
马素霞¹

1.
太原理工大学电气与动力工程学院，太原 030024
2.
煤电清洁控制教育部重点实验室，太原 030024
3.
中北大学能源与动力工程学院，太原 030051

(我刊青年编委李勇来稿)

基金项目:

山西省基础研究计划青年基金 202203021212263

中国博士后科学基金(面上项目) 2023M732569

山西省回国留学人员科研资助项目 2023-055

山西省回国留学人员科研资助项目 2023-143

教育部“春晖计划”合作科研项目 202200075

详细信息

通讯作者:
李勇(1987—)，男，讲师，博士(通讯作者. E-mail: yongli@tyut.edu.cn)

中图分类号: O35;V19
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出版历程
- 收稿日期: 2023-11-06
- 修回日期: 2024-04-23
- 刊出日期: 2024-05-01

Experimental Study on Flow and Heat Transfer Characteristics of Ambient Air in NACA0021 and NACA4822 Airfoil-Fin Channels

1.
College of Electrical and Power Engineering, Taiyuan University of Technology, Taiyuan 030024, P.R.China
2.
Key Laboratory of Cleaner Intelligent Control on Coal & Electricity, Ministry of Education, Taiyuan 030024, P.R.China
3.
School of Energy and Power Engineering, North University of China, Taiyuan 030051, P.R.China

(Contributed by LI Yong, M. AMM Youth Editorial Board)

摘要

摘要: 针对超燃冲压发动机在更高Mach数飞行时，主动再生冷却技术面临换热能力不足的瓶颈问题，拟利用翼型肋加强再生冷却通道的传热性能.为了从原理上验证翼型肋通道的强化传热效果，搭建了环境空气在NACA0021对称翼型肋和NACA4822非对称翼型肋通道(横截面尺寸50 mm × 50 mm)中的流动传热实验测试平台，基于稳态液晶技术得到受热表面的Nusselt数.通过实验研究发现：NACA0021对称翼型肋通道和NACA4822非对称翼型肋通道的传热强度分别被提升了0.17%~17.1%和18.4%~52.1%，50 m³/h流量下的PEC(performance evaluation criterion)分别为1.04和1.24；大流量条件下，NACA4822非对称翼型肋通道可强化中间受热面的传热性能；翼型肋通道中的流动压降也会相应增大，其中NACA4822翼型肋通道中的压降最大，翼型肋的非对称性使得流动湍流强度不断积累造成下游压降存在明显升高.该研究将有助于进一步开展翼型肋通道内超临界流体的流动传热特性研究，拓宽超燃冲压发动机主动再生冷却技术的应用温区.
- 超燃冲压发动机 /
- 翼型肋通道 /
- Nusselt数 /
- 压力损失
Abstract: The active regenerative cooling technology faces the bottleneck problem of insufficient heat transfer capacity when the scramjet flies at a higher Mach number. It is proposed to strengthen the heat transfer performance of the regenerative cooling channel with airfoil-fins. To verify the enhanced heat transfer effect of the airfoil-fin channel in principle, an experimental test platform for flow and heat transfer of ambient air in NACA0021 symmetrical airfoil-fin channels and NACA4822 asymmetric airfoil-fin channels (with cross-section sizes of 50 mm × 50 mm) was built. The Nusselt number of the heated surface was obtained based on the steady-state liquid crystal technique. The results show that, the heat transfer intensities of NACA0021 symmetrical airfoil-fin channels and NACA4822 asymmetric airfoil-fin channels improve by 0.17%~17.1% and 18.4%~52.1%, respectively. Correspondingly, PECs are 1.04 and 1.24, respectively, with the volume flow of ambient air at 50 m³/h. The NACA4822 asymmetric airfoil-fin channel can enhance the heat transfer performance of the middle heating surface under the condition of a large flow rate. The flow pressure drop in the airfoil-fin channels also increases correspondingly, where the pressure drop in the NACA4822 airfoil-fin channel is the largest. The asymmetry of the airfoil-fin causes the continuous accumulation of flow turbulence intensity, resulting in a significant increase in the downstream pressure drop. The work is helpful for further research on the flow and heat transfer characteristics of supercritical fluids in airfoil-fin channels, and broadens the application temperature range of the active regenerative cooling technology for scramjets.
- scramjet engine /
- airfoil-fin channel /
- Nusselt number /
- pressure loss
edited-by

edited-by
注释:

1) (我刊青年编委李勇来稿)

HTML全文

图 1 超燃冲压发动机再生冷却原理图

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 1. Schematic diagram of regenerative cooling of the scramjet engine

下载: 全尺寸图片幻灯片

图 2 超临界(压力)正癸烷的热物性参数

Figure 2. Thermal properties of supercritical (pressure) n-decane

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图 3 单壁面受热矩形通道内超临界(压力)碳氢燃料传热恶化现象

Figure 3. Heat transfer deterioration of supercritical (pressure) hydrocarbon fuel in a rectangular channel heated on a single wall

下载: 全尺寸图片幻灯片

图 4 翼型肋通道中，环境空气流动传热实验测试平台

Figure 4. The experimental test platform for flow and heat transfer of ambient air in an airfoil-fin channel

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图 5 翼型肋排布方式(单位: mm)

Figure 5. The arrangement of the airfoil-fin (unit: mm)

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图 6 液晶标定示意图

Figure 6. The liquid crystal calibration diagram

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图 7 液晶色随温度变化图

Figure 7. The color change of liquid crystal with the temperature

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图 8 翼型肋结构图

Figure 8. Structure diagram of the airfoil-fin

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图 9 NACA0021翼型肋通道和光滑通道受热表面的Nusselt数分布

Figure 9. Nusselt number distributions on heated surfaces of the NACA0021 airfoil-fin channel and the smooth channel

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图 10 NACA4822翼型肋通道和光滑通道受热表面的Nusselt数分布

Figure 10. Nusselt number distributions on heated surfaces of the NACA4822 airfoil-fin channel and the smooth channel

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图 11 无翼型肋、NACA0021翼型肋和NACA4822翼型肋通道中受热表面沿程平均Nusselt数分布

Figure 11. Average Nusselt number distributions along the heated surface in the smooth channel the NACA0021 airfoil-fin and the NACA4822 airfoil-fin

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图 12 无翼型肋、NACA0021翼型肋和NACA4822翼型肋通道中沿程压降

Figure 12. Pressure drops along the smooth channel, the NACA0021 airfoil-fin and the NACA4822 airfoil-fin

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图 13 NACA0021翼型肋和NACA4822翼型肋通道中传热-压降综合性能分析

Figure 13. Comprehensive performance analysis of heat transfer and pressure drop in the NACA0021 airfoil-fin and the NACA4822 airfoil-fin channels

下载: 全尺寸图片幻灯片

表 1 实验仪器详细信息

Table 1. Details of laboratory instruments

	experimental apparatus	manufacturer	product model	measuring range	measuring error
measuring apparatus	CCD camera	Allied Vision (Germany)	Prosilica GE 1650C	4 096×22 160 pixels	-
	float flowmeter	KROHNE (Germany)	VA20R	0~210 N·m³/h	2%
	micromanometer	Furness Controls (UK)	FC014	0~10 000 Pa	1%
	thermometer	Steinfurth (Germany)	DTM Spezial	15~61 ℃	0.01 ℃
test instrument	centrifugal fan	Siemens (Germany)	ELMO-G 2BH3 110-0HC42-5	1.10 kW/50 Hz	-
	thermalized foil	-	PI108920-00	24 V/60 W	-
	liquid crystal membrane	LCR Hallcrest Ltd. (UK)	R35C5W	-	0.1 K
	DC power	EVENTEK (France)	KPS305D	0~32 V/0~6 A	-

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