航空发动机进口帽罩综合加热效果实验研究

蒋新伟; 周建军; 贾琦; 李云单; 许卫疆

doi:10.13224/j.cnki.jasp.20220918

航空发动机进口帽罩综合加热效果实验研究

doi: 10.13224/j.cnki.jasp.20220918

蒋新伟^1,,
周建军¹,
贾琦¹,
李云单¹,
许卫疆^2,*, ,

1.
中国航发沈阳发动机研究所，沈阳 110015
2.
西北工业大学动力与能源学院，西安 710072

详细信息

作者简介:
蒋新伟（1992-），男，工程师，硕士，主要从事航空发动机防冰系统研究

通讯作者:
许卫疆（1974-），男，副教授，博士，主要从事航空发动机高温部件冷却技术研究。E-mail：xuweijiang@nwpu.edu.cn

中图分类号: V233.94
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- 被引次数: 0
出版历程
- 收稿日期: 2022-11-29
- 网络出版日期: 2025-01-07

Experimental investigation on overall heating effect of aero-engine inlet cone

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
为了研究不同气流参数对发动机进口帽罩综合加热效果的影响，采用红外成像测温技术对帽罩全表面综合加热效率进行了测量，并详细分析了实验帽罩在二次流吹风比为0.8～3.0、温比为1.2～1.6和主流雷诺数为8600～17000条件下的综合加热效果。实验结果表明：在内部冲击和外部气膜的共同作用下，帽罩前缘具有较高的加热效率，约为0.5；在实验条件下，提高二次流热气的吹风比能够有效地增强帽罩全表面的加热效果，当吹风比由0.8增大到2.0，综合加热效率平均提高33%；二次流温度的提高，对帽罩前缘加热效果影响较小，综合加热效率增幅只有0.01左右；随着主流雷诺数增加，帽罩中后部的综合加热效率明显降低。
- 红外热成像测温 /
- 帽罩 /
- 防冰 /
- 加热效果 /
- 吹风比
Abstract:
In order to study the influence of flow parameters on overall heating effect of aero-engine inlet cone, the comprehensive heating efficiency on cone surface was measured by infrared temperature measurement technology. The overall heating effect of experimental cone was analyzed in detail under the conditions that the secondary flow blowing ratio was within the range of 0.8—3.0, the temperature ratio was from 1.2 to 1.6, and the mainstream Reynolds number was from 8600 to 17000. The experimental results showed that both internal heat transfer and external film heating caused a high heating efficiency at the leading edge, which was about 0.5. Under experimental conditions, improving blowing ratio can bring better heating effect of the full cone surface. The increase of the blowing ratio from 0.8 to 2.0 can result in a gain of about 33% for the heating effect. The increase of secondary flow temperature can increase the heating effect of leading edge slightly by about 0.01 in comprehensive heating efficiency. The increase of mainstream Reynolds number can decrease the heating effect of the middle and rear parts for the cone.
- infrared thermal imaging test temperature /
- cone /
- anti-icing /
- heating effect /
- blowing ratio

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图 1 实验系统

Figure 1. Experimental system

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图 2 典型帽罩热气流路

Figure 2. Hot air passage for typical cone

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图 3 帽罩实验件

Figure 3. Cone piece

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图 4 红外测温校准曲线

Figure 4. Infrared temperature calibration curve

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图 5 典型帽罩表面综合加热效果

Figure 5. Comprehensive heating effect of typical cone surface

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图 6 不同吹风比时帽罩综合加热效率

Figure 6. Overall heating efficiency of cone surface with different blowing ratios

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图 7 不同吹风比时帽罩综合加热效率对比曲线

Figure 7. Overall heating efficiency contrast curves of cone surface with different blowing ratios

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图 8 不同温比时帽罩综合加热效率

Figure 8. Overall heating efficiency of cone surface with different temperature ratios

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图 9 不同温比时帽罩综合加热效率对比曲线

Figure 9. Overall heating efficiency contrast curves of cone surface with different temperature ratios

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图 10 不同主流雷诺数时帽罩综合加热效率

Figure 10. Overall heating efficiency of cone surface with different mainstream Reynolds number

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图 11 不同主流雷诺数时帽罩综合加热效率对比曲线

Figure 11. Overall heating efficiency contrast curves of cone surface with different mainstream Reynolds number

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参考文献(20)

[1]	裘燮纲,韩凤华. 飞机防冰系统[M]. 北京: 北京航空教材编审组,1985. QIU Xiegang,HAN Fenghua. Aircraft anti-icing system[M]. Beijing: Aviation Industry Press,1985. (in Chinese QIU Xiegang, HAN Fenghua. Aircraft anti-icing system[M]. Beijing: Aviation Industry Press, 1985. (in Chinese)
[2]	PLANQUART P,VANDEN BORRE G,BUCHLIN J M. Experimental and numerical optimization of a wing leading edge hot air anti-icing system: AIAA 2005-1277 [C]//Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston,Virigina: AIAA,2005: 494-496.
[3]	ELANGOVAN R,HUNG K E. Minimum heating energy requirements of piccolo tube jet impingement thermal anti-icing system[C]//Proceedings of ASME/JSME 2007 Thermal Engineering Heat Transfer Summer Conference Collocated,Vancouver: ASME/JSME,2009: 959-967.
[4]	ANDREOZZI A,LUCIBELLO F,MANCA O,et al. Thermal and fluid dynamic analysis on impinging jet for aircraft anti-icing[C]//Proceedings of ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis,Istanbul: ASME,2010: 749-756.
[5]	IMBRIALE M,IANIRO A,MEOLA C,et al. Convective heat transfer by a row of jets impinging on a concave surface[J]. International Journal of Thermal Sciences,2014,75: 153-163. doi: 10.1016/j.ijthermalsci.2013.07.017
[6]	张敏. 发动机进口支板三维防冰数值模拟与试验研究[D]. 南京: 南京航空航天大学,2019. ZHANG Min. Numerical simulation and experimental study on three-dimensional anti-icing of engine inlet support plate[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2019. (in Chinese ZHANG Min. Numerical simulation and experimental study on three-dimensional anti-icing of engine inlet support plate[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese)
[7]	雷桂林. 电热防冰除冰及冰融化相变换热机理研究[D]. 上海: 上海交通大学,2017. LEI Guilin. Study on the mechanism of electric anti-icing and ice melting phase change heat transfer[D]. Shanghai: Shanghai Jiao Tong University,2017. (in Chinese LEI Guilin. Study on the mechanism of electric anti-icing and ice melting phase change heat transfer[D]. Shanghai: Shanghai Jiao Tong University, 2017. (in Chinese)
[8]	雷桂林,郑梅,董威,等. 航空发动机进气支板电热防冰试验[J]. 航空学报,2017,38(8): 49-60. LEI Guilin,ZHENG Mei,DONG Wei,et al. Test on electrothermal anti-icing of aero-engine inlet strut[J]. Acta Aeronautica et Astronautica Sinica,2017,38(8): 49-60. (in Chinese LEI Guilin, ZHENG Mei, DONG Wei, et al. Test on electrothermal anti-icing of aero-engine inlet strut[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(8): 49-60. (in Chinese)
[9]	董威,朱剑鋆,周志翔,等. 航空发动机支板热滑油防冰性能试验[J]. 航空学报,2014,35(7): 1845-1853. DONG Wei,ZHU Jianjun,ZHOU Zhixiang,et al. Test on performance of an aero-engine strut hot lubrication oil anti-icing system[J]. Acta Aeronautica et Astronautica Sinica,2014,35(7): 1845-1853. (in Chinese DONG Wei, ZHU Jianjun, ZHOU Zhixiang, et al. Test on performance of an aero-engine strut hot lubrication oil anti-icing system[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(7): 1845-1853. (in Chinese)
[10]	唐管财. 航空发动机进口支板热气防冰数值模拟研究[D]. 北京: 北京交通大学,2021. TANG Guancai. Numerical simulation study on hot air anti-icing of aero-engine inlet support plate[D]. Beijing: Beijing Jiaotong University,2021. (in Chinese TANG Guancai. Numerical simulation study on hot air anti-icing of aero-engine inlet support plate[D]. Beijing: Beijing Jiaotong University, 2021. (in Chinese)
[11]	李云单,陆海鹰,朱惠人. 航空发动机热气防冰结构的冲击换热特性研究[J]. 航空发动机,2011,37(5): 16-20,52. LI Yundan,LU Haiying,ZHU Huiren. Study of impacting heat transfer characteristic for aeroengine heat anti-icing structure[J]. Aeroengine,2011,37(5): 16-20,52. (in Chinese LI Yundan, LU Haiying, ZHU Huiren. Study of impacting heat transfer characteristic for aeroengine heat anti-icing structure[J]. Aeroengine, 2011, 37(5): 16-20, 52. (in Chinese)
[12]	关涛,张靖周,单勇,等. 楔形凹腔内带前伸槽冲击板射流冲击换热[J]. 航空动力学报,2017,32(3): 592-598. GUAN Tao,ZHANG Jingzhou,SHAN Yong,et al. Impingement heat transfer inside wedge-shaped concave by jets from impingment plate with front-extended port[J]. Journal of Aerospace Power,2017,32(3): 592-598. (in Chinese GUAN Tao, ZHANG Jingzhou, SHAN Yong, et al. Impingement heat transfer inside wedge-shaped concave by jets from impingment plate with front-extended port[J]. Journal of Aerospace Power, 2017, 32(3): 592-598. (in Chinese)
[13]	柯鹏,张韵,于广锋,等. 航空发动机进口支板外部热气膜对水滴撞击特性的影响[J]. 航空动力学报,2017,32(3): 621-629. KE Peng,ZHANG Yun,YU Guangfeng,et al. Influence of exterior hot-film on droplet impingement characteristics over aero-engine inlet strut[J]. Journal of Aerospace Power,2017,32(3): 621-629. (in Chinese KE Peng, ZHANG Yun, YU Guangfeng, et al. Influence of exterior hot-film on droplet impingement characteristics over aero-engine inlet strut[J]. Journal of Aerospace Power, 2017, 32(3): 621-629. (in Chinese)
[14]	柯鹏,杨慧赟,王俊凯,等. 航空发动机帽罩热气膜防冰的加热特性[J]. 航空动力学报,2018,33(3): 530-539. KE Peng,YANG Huiyun,WANG Junkai,et al. Heating characteristics of aero-engine nose cone with film-heating anti-icing system[J]. Journal of Aerospace Power,2018,33(3): 530-539. (in Chinese KE Peng, YANG Huiyun, WANG Junkai, et al. Heating characteristics of aero-engine nose cone with film-heating anti-icing system[J]. Journal of Aerospace Power, 2018, 33(3): 530-539. (in Chinese)
[15]	刘华,郭文,杨军,等. 发动机进气帽罩防冰热载荷的数值模拟研究[J]. 燃气涡轮试验与研究,2012,25(1): 44-48. LIU Hua,GUO Wen,YANG Jun,et al. Numerical investigation of anti-icing thermal loads for engine inlet cowl[J]. Gas Turbine Experiment and Research,2012,25(1): 44-48. (in Chinese LIU Hua, GUO Wen, YANG Jun, et al. Numerical investigation of anti-icing thermal loads for engine inlet cowl[J]. Gas Turbine Experiment and Research, 2012, 25(1): 44-48. (in Chinese)
[16]	侯会文,范顺昌,李昕,等. 单孔冲击式帽罩前缘流动换热特性数值分析[J]. 航空发动机,2020,46(1): 32-37. HOU Huiwen,FAN Shunchang,LI Xin,et al. Numerical analysis of flow heat transfer characteristics of leading edge of single-hole impact cone[J]. Aeroengine,2020,46(1): 32-37. (in Chinese HOU Huiwen, FAN Shunchang, LI Xin, et al. Numerical analysis of flow heat transfer characteristics of leading edge of single-hole impact cone[J]. Aeroengine, 2020, 46(1): 32-37. (in Chinese)
[17]	张丽芬,葛鑫,张斐,等. 旋转帽罩结冰相似准则的冰风洞试验研究[J]. 实验流体力学,2021,35(4): 52-59. ZHANG Lifen,GE Xin,ZHANG Fei,et al. An ice wind tunnel test study on the scaling law of a rotating cone[J]. Journal of Experiments in Fluid Mechanics,2021,35(4): 52-59. (in Chinese ZHANG Lifen, GE Xin, ZHANG Fei, et al. An ice wind tunnel test study on the scaling law of a rotating cone[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(4): 52-59. (in Chinese)
[18]	高艳欣,周建军,李云单,等. 吹气式旋转帽罩防冰特性[J]. 南京航空航天大学学报,2016,48(3): 359-365. GAO Yanxin,ZHOU Jianjun,LI Yundan,et al. Anti-icing properties of blowing rotating spinner[J]. Journal of Nanjing University of Aeronautics & Astronautics,2016,48(3): 359-365. (in Chinese GAO Yanxin, ZHOU Jianjun, LI Yundan, et al. Anti-icing properties of blowing rotating spinner[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2016, 48(3): 359-365. (in Chinese)
[19]	徐超. 旋转帽罩热气防冰试验研究与三维数值模拟[D]. 南京: 南京航空航天大学,2021. XUN Chao. Experimental study and three-dimensional numerical simulation of hot air anti-icing for rotating hood[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2021. (in Chinese XUN Chao. Experimental study and three-dimensional numerical simulation of hot air anti-icing for rotating hood[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021. (in Chinese)
[20]	傅亮,陈勇,王安正. 旋转帽罩表面积冰甩脱位置的数值模拟[J]. 航空发动机,2016,42(5): 70-75. FU Liang,CHEN Yong,WANG Anzheng. Numerical simulation of ice shedding from spinning cone[J]. Aeroengine,2016,42(5): 70-75. (in Chinese FU Liang, CHEN Yong, WANG Anzheng. Numerical simulation of ice shedding from spinning cone[J]. Aeroengine, 2016, 42(5): 70-75. (in Chinese)