热气冲击射流换热特性与防冰效果

doi:10.7527/S1000-6893.2025.32653

Abstract

Abstract:

This study presents a combined test and numerical investigation of heat transfer characteristics and anti-icing performance of a nacelle hot-air anti-icing system， which employs a double-row impinging jet configuration integrated with a piccolo tube. High-resolution Nusselt number distributions on the inner surface of the anti-icing cavity were obtained by using transient thermochromic liquid crystal thermography over a Reynolds number range of 15 000 to 40 000， leading to the establishment of a heat transfer correlation model suitable for engineering applications. Through internal-to-external conjugate heat transfer simulations， the anti-icing temperature distributions under typical nacelle operating conditions were further analyzed. The results demonstrate that increasing the Reynolds number from 15 000 to 40 000 enhances the average Nusselt number at the inner lip surface by a factor of 2.4 and raises the hot-air consumption by approximately 2.7 times， whereas the average anti-icing surface temperature increases by only 28.4 ℃. These findings indicate that merely increasing hot-air mass flow provides limited improvement in anti-icing efficiency and highlight substantial potential for reducing air consumption through structural optimization and heat transfer enhancement. Moreover， variations in the angle of attack significantly influence anti-icing performance， as a 5.6° angle of attack reduces the average surface temperature by approximate 13.6 ℃ compared to the 0° condition， underscoring the importance of optimizing jet arrangement to align with regions experiencing the highest icing loads.

Key words: aircraft engine, nacelle, hot-air anti-icing, impingement heat transfer, transient liquid crystal

CLC Number:

Yuyang LIU, Xinbo DAI, Qiang WANG, Xian YI. Heat transfer characteristics and anti-icing performance of hot-air impingement jets[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(12): 132653.

Figures/Tables 17

Fig.1

Fig.2

Fig.3

Table 1

Fig.4

Fig.5

Fig.6

Table 2

Fig.8

Fig.9

Fig.10

Fig.11

Table 3

Deviations of Nu¯ on internal lip surface between computation result and measured data

Re	$N u ¯$		偏差/%
Re	数值计算	试验	偏差/%
15 000	42.3	39.2	7.9
20 000	55.1	50.0	10.2
25 000	66.2	61.2	8.2
30 000	75.4	71.7	5.2
35 000	86.6	82.1	5.5
40 000	98.7	92.1	7.2

Table 3

Fig.12

Fig.13

References 29

[1]	林贵平. 飞机结冰与防冰技术［M］. 北京：北京航空航天大学出版社， 2016.
	LIN G P. Aircraft icing and anti-icing technology［M］. Beijing： Beijing University of Aeronautics Astronautics Press， 2016 （in Chinese）.
[2]	CALISKAN F， HAJIYEV C. A review of in-flight detection and identification of aircraft icing and reconfigurable control［J］. Progress in Aerospace Sciences， 2013， 60： 12-34.
[3]	桂业伟，周志宏，李颖晖，等. 关于飞机结冰的多重安全边界问题［J］. 航空学报， 2017， 38（2）： 520734.
	GUI Y W， ZHOU Z H， LI Y H， et al. Multiple safety boundaries protection on aircraft icing［J］. Acta Aeronautica et Astronautica Sinica， 2017， 38（2）： 520734 （in Chinese）.
[4]	朱永峰，方玉峰，封文春. 某型飞机发动机短舱防冰系统设计计算［J］. 航空动力学报， 2012， 27（6）： 1326-1331.
	ZHU Y F， FANG Y F， FENG W C. Design and calculation of aircraft nacelle anti-icing system［J］. Journal of Aerospace Power， 2012， 27（6）： 1326-1331 （in Chinese）.
[5]	杨倩，董威，郭之强，等. 涡扇发动机短舱结冰试验相似方法［J］. 航空动力学报， 2019， 34（9）： 1988-2000.
	YANG Q， DONG W， GUO Z Q， et al. Scaling method of turbofan engine nacelle under icing test［J］. Journal of Aerospace Power， 2019， 34（9）： 1988-2000 （in Chinese）.
[6]	MARTIN E L， WRIGHT L M， CRITES D C. Computational investigation of jet impingement on turbine blade leading edge cooling with engine-like temperatures［C］∥ ASME Turbo Expo 2012. New York： American Society of Mechanical Engineers， 2012： 311-322.
[7]	CHUPP R E， HELMS H E， MCFADDEN P W， et al. Evaluation of internal heat-transfer coefficients for impingement-cooled turbine airfoils［J］. Journal of Aircraft， 1969， 6（3）： 203-208.
[8]	MARTIN E L， WRIGHT L M， CRITES D C. Impingement heat transfer enhancement on a cylindrical， leading edge model with varying jet temperatures［J］. Journal of Turbomachinery， 2013， 135（3）： 031021.
[9]	REN Z， VANGA S R， ROGERS N， et al. Internal and external cooling of a full coverage effusion cooling plate： Effects of double wall configuration and conditions［J］. International Journal of Thermal Sciences， 2018， 124： 36-49.
[10]	TERZIS A， SKOURIDES C， OTT P， et al. Aerothermal investigation of a single row divergent narrow impingement channel by particle image velocimetry and liquid crystal thermography［J］. Journal of Turbomachinery， 2016， 138（5）： 051003.
[11]	TERZIS A. On the correspondence between flow structures and convective heat transfer augmentation for multiple jet impingement［J］. Experiments in Fluids， 2016， 57（9）： 146.
[12]	SINGH P， EKKAD S V. Effects of spent air removal scheme on internal-side heat transfer in an impingement-effusion system at low jet-to-target plate spacing［J］. International Journal of Heat and Mass Transfer， 2017， 108： 998-1010.
[13]	RAO Y， LIU Y Y， WAN C Y. Multiple-jet impingement heat transfer in double-wall cooling structures with pin fins and effusion holes［J］. International Journal of Thermal Sciences， 2018， 133： 106-119.
[14]	KIM S H， AHN K H， PARK J S， et al. Local heat and mass transfer measurements for multi-layered impingement/effusion cooling： Effects of pin spacing on the impingement and effusion plate［J］. International Journal of Heat and Mass Transfer， 2017， 105： 712-722.
[15]	ROGERS N， REN Z， BUZZARD W， et al. Effects of double wall cooling configuration and conditions on performance of full-coverage effusion cooling［J］. Journal of Turbomachinery， 2017， 139（5）： 051009.
[16]	刘秀芳，陈佳军，郑勉，等. 新型高效机载电子器件冷却系统设计及实验［J］. 航空学报， 2025， 46（9）： 131078.
	LIU X F， CHEN J J， ZHENG M， et al. Design and experiment of a new efficient cooling system for airborne electronic devices［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（9）：131078 （in Chinese）.
[17]	韦宏，王鹏，董威，等. 主流速度对微细管式预冷器结霜和抑霜特性的影响［J］. 航空学报， 2024， 45（2）： 128639.
	WEI H， WANG P， DONG W， et al. Effects of main flow velocity on frosting and defrosting characteristics of microtubule precooler［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（2）： 128639 （in Chinese）.
[18]	刘森云，王桥，易贤，等. 3 m×2 m结冰风洞试验技术新进展（2020—2022年）［J］. 空气动力学学报， 2023， 41（1）： 57-65.
	LIU S Y， WANG Q， YI X， et al. New progress of 3 m × 2 m icing wind tunnel test technology from 2020 to 2022［J］. Acta Aerodynamica Sinica， 2023， 41（1）： 57-65 （in Chinese）.
[19]	易贤，任靖豪，赖庆仁，等. 大型飞机全尺寸多段翼结冰特性计算和试验［J］. 航空学报， 2025， 46（5）： 531575.
	YI X， REN J H， LAI Q R， et al. Icing characteristics of full-scale multi-element configurations of large aircraft： Computation and experiment［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（5）： 531575 （in Chinese）.
[20]	WANG Q， CHEN N L， WANG Y B， et al. Scallop ice shape characteristics of swept wing based on large-scale icing wind tunnel experiment［J］. Chinese Journal of Aeronautics， 2023， 36（12）： 214-230.
[21]	饶宇，刘宇阳，万超一. 具有气膜出流孔和针肋的双层壁冷却结构内的冲击传热性能［J］. 航空学报， 2018， 39（1）： 121418.
	RAO Y， LIU Y Y， WAN C Y. Jet impingement heat transfer performance in a double-wall cooling structure with film effusion holes and pin fins［J］. Acta Aeronautica et Astronautica Sinica， 2018， 39（1）： 121418 （in Chinese）.
[22]	IRELAND P T， JONES T V. Liquid crystal measurements of heat transfer and surface shear stress［J］. Measurement Science and Technology， 2000， 11（7）： 969-986.
[23]	BUTTSWORTH D R， JONES T V. Radial conduction effects in transient heat transfer experiments［J］. The Aeronautical Journal， 1997， 101（1005）： 209-212.
[24]	XING Y F， SPRING S， WEIGAND B. Experimental and numerical investigation of heat transfer characteristics of inline and staggered arrays of impinging jets［J］. Journal of Heat Transfer， 2010， 132（9）： 092201.
[25]	LIU Y Y， RAO Y， WEIGAND B. Heat transfer and pressure loss characteristics in a swirl cooling tube with dimples on the tube inner surface［J］. International Journal of Heat and Mass Transfer， 2019， 128： 54-65.
[26]	JECK R. Icing design envelopes （14 CFR Parts 25 and 29， Appendix C） converted to a distance-based format： DOT/FAA/AR-00/30［R］. Washington， D.C.： Federal Aviation Administration， 2002.
[27]	KERCHER D M， TABAKOFF W. Heat transfer by a square array of round air jets impinging perpendicular to a flat surface including the effect of spent air［J］. Journal of Engineering for Power， 1970， 92（1）： 73-82.
[28]	CHI Z R， KAN R， REN J， et al. Experimental and numerical study of the anti-crossflows impingement cooling structure［J］. International Journal of Heat and Mass Transfer， 2013， 64： 567-580.
[29]	LIU Y Y， YANG Q， WANG Q， et al. Investigations on optimization and verification of nacelle hot air anti-icing system in a large icing wind tunnel［J］. Aerospace Science and Technology， 2025， 163： 110312.

参数	数值	参数	数值
D/m	0.01	α/（°）	±15
R/m	0.06	Re	15 000~40 000
S/m	0.05	S/D	5.0
H/m	0.03	H/D	3.0
L/m	0.01	L/D	1.0

工况	LWC/（g·m^-3）	MVD/μm	V/（m·s^-1）	攻角/（°）	T_s/℃	T_h/℃
1	0.455	20.0	134.7	0	-8.6	145.0
2	0.455	20.0	134.7	5.6	-8.6	145.0
3	0.374	20.0	134.7	4.6	-12.4	145.0
4	0.437	21.4	140.0	4.6	-16.7	145.0

Heat transfer characteristics and anti-icing performance of hot-air impingement jets

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