热气防冰系统热载荷及引气流量制度分析

王柳; 曾腾辉; 任哲钒; 章涛; 黄平; 卜雪琴

doi:10.13700/j.bh.1001-5965.2021.0710

热气防冰系统热载荷及引气流量制度分析

doi: 10.13700/j.bh.1001-5965.2021.0710

王柳¹,
曾腾辉¹,
任哲钒²,
章涛¹,
黄平³,
卜雪琴^3, ,

1.
中国航空工业集团公司武汉航空仪表有限责任公司，武汉 430074
2.
中国商用飞机有限责任公司上海飞机设计研究院，上海 201210
3.
北京航空航天大学航空科学与工程学院，北京 100191

详细信息

通讯作者:
E-mail：buxueqin@buaa.edu.cn

中图分类号: V244.1+5
计量
- 文章访问数: 179
- HTML全文浏览量: 31
- PDF下载量: 19
- 被引次数: 0
出版历程
- 收稿日期: 2021-11-24
- 录用日期: 2022-03-27
- 网络出版日期: 2022-04-08
- 整期出版日期: 2023-10-31

Analysis of heat load and bleed air schedule for hot air anti-icing system

1.
Wuhan Aviation Instrument Corporation Ltd.，Aviation Industry Corporation of China，Wuhan 430074，China
2.
Shanghai Aircraft Design and Research Institute，Commercial Aircraft Corporation of China Ltd.，Shanghai 201210，China
3.
School of Aeronautic Science and Engineering，Beihang University，Beijing 100191，China

More Information

Corresponding author: E-mail：buxueqin@buaa.edu.cn

摘要

摘要:
飞机机翼热气防冰系统设计主要包括防冰热载荷计算、笛形管设计、防冰腔设计和防冰系统验证。以某客机机翼为例，在机翼防冰热载荷计算的基础上，分析热载荷及溢流水蒸发率结果，获得防冰引气量需求，进一步提出防冰系统随高度变化的引气流量制度，确定防冰系统严酷状态设计点。采用欧拉-欧拉两相流方法计算水滴运动和表面水滴撞击特性，建立考虑溢流水流动相变的机翼表面的能量平衡方程，计算分析机翼表面的防冰热载荷和溢流水的蒸发率。分析结果表明：同一飞行与结冰气象条件下，在防冰表面温度2~15 ℃范围，热载荷随着表面温度近似以线性增加；为满足防冰要求，高度较低时的状态对应的表面温度设计值较大；引气流量制度随高度变化分为3个阶段：高度小于5594.9 m时，单边流量为0.91 kg/s；高度大于6705.0 m时，单边流量为0.59 kg/s；中间高度对应流量采取两者线性插值方式。研究结果为热气防冰系统的笛行管设计及校核提供支撑。
- 机翼 /
- 热气防冰系统 /
- 热载荷 /
- 设计状态点 /
- 引气流量制度
Abstract:
The design of an aircraft wing anti-icing system mainly includes the anti-icing heat load calculation, piccolo tube design, anti-icing cavity design, and anti-icing system verification. This paper introduces the first part of a series study in this respect. With an aircraft wing as an example, the heat load and the runback water evaporation rate are analyzed based on the calculation of the wing anti-icing heat load, and the demand of the bleed air for anti-icing is then obtained. Furthermore, a bleed air schedule for anti-icing varying with altitude is proposed, and severe conditions for the anti-icing system design are determined. The Euler-Euler two-phase flow method is used to calculate the water droplet movement and impingement characteristics on the wing surface. The energy balance equation of the wing surface considering the phase change of runback water is then established, and the anti-icing heat load and evaporation rate of the wing surface are obtained. The results show that the heat load increases approximately linearly with the surface temperature in the range of 2~15 ℃ under the same flight and icing condition. To meet the anti-icing requirements, the design value of the surface temperature corresponding to the lower altitude is increased. The bleed air schedule for anti-icing varying with altitude is divided into three stages: the hot air flow flux is 0.91 kg/s when the altitude is less than 18356 ft, 0.59 kg/s when the altitude is higher than 21998 ft and linearly interpolated when the altitude is in between 18356 and 21998 ft. The results of this study provide valuable insight into the design and verification of the piccolo tube of hot air anti-icing systems.
- wing /
- hot air anti-icing system /
- heat load /
- design condition /
- bleed air schedule

HTML全文

图 1 防冰系统表面的热流示意图

Figure 1. Schematic of heat flux on anti-icing surface

下载: 全尺寸图片幻灯片

图 2 防冰表面控制容积的质量守恒

Figure 2. Mass conservation of control volume on anti-icing surface

下载: 全尺寸图片幻灯片

图 3 防冰表面控制容积的能量守恒

Figure 3. Energy conservation of control volume on anti-icing surface

下载: 全尺寸图片幻灯片

图 4 机翼几何模型

Figure 4. Geometric model of wing

下载: 全尺寸图片幻灯片

图 5 整体网格

Figure 5. Global mesh

下载: 全尺寸图片幻灯片

图 6 机翼表面网格

Figure 6. Mesh on wing surface

下载: 全尺寸图片幻灯片

图 7 状态点在结冰包线中的分布

Figure 7. Distribution of operating points in icing envelope

下载: 全尺寸图片幻灯片

图 8 溢流水结果云图

Figure 8. Contours of runback water

下载: 全尺寸图片幻灯片

图 9 防冰热载荷云图

Figure 9. Contours of anti-icing heatload

下载: 全尺寸图片幻灯片

图 10 表面温度为10 ℃时的热载荷随高度变化

Figure 10. Heatload changes with altitude (T = 10 ℃)

下载: 全尺寸图片幻灯片

图 11 热载荷与表面温度之间的关系(Case3)

Figure 11. Relationship between heatload and surface temperature (Case3)

下载: 全尺寸图片幻灯片

图 12 蒸发率与表面温度关系(Case3)

Figure 12. Relationship between evaporation rate and surface temperature (Case3)

下载: 全尺寸图片幻灯片

图 13 防冰热载荷和高度的关系

Figure 13. Relationship between anti-icing heatload and altitude

下载: 全尺寸图片幻灯片

图 14 引气流量和高度的关系

Figure 14. Relationship between bleed air flow flux and altitude

下载: 全尺寸图片幻灯片

表 1 飞行与结冰条件

Table 1. Flight and icing conditions

编号	高度/m	温度/℃	迎角/(°)	速度/ (m·s⁻¹)	L_MVD/ μm	S_LWC/ (g·m⁻³)
Case1	450	−4.70	4.80	118.10	20	0.54
Case2	550	−3.60	4.90	103.40	20	0.56
Case3	950	−4.90	4.70	121.10	20	0.53
Case4	1250	−4.50	4.80	116.10	20	0.54
Case5	1550	−5.20	4.70	124.60	20	0.53
Case6	1850	−4.80	4.80	119.50	20	0.53
Case7	2150	−3.30	6.30	99.60	20	0.56
Case8	2250	−4.10	4.80	110.50	20	0.55
Case9	2450	−3.80	6.20	106.70	20	0.55
Case10	2450	−5.20	4.70	125.10	20	0.53
Case11	2850	−4.30	4.80	113.90	20	0.54
Case12	3150	−5.00	4.80	121.80	20	0.53
Case13	3250	−3.50	8.00	102.90	20	0.56
Case14	3450	−4.60	4.80	117.50	20	0.54
Case15	3750	−5.30	4.70	125.70	20	0.52
Case16	4050	−3.20	7.80	97.30	20	0.57
Case17	4450	−5.60	4.40	143.00	24	0.42
Case18	5250	−10.45	8.00	116.90	20	0.42
Case19	5450	−11.76	7.80	112.20	20	0.39
Case20	5550	−12.42	7.90	105.00	20	0.38
Case21	5950	−15.04	8.30	118.40	20	0.32
Case22	6050	−15.70	7.80	107.50	20	0.30
Case23	6705	−20.00	9.00	119.10	20	0.21
Case24	4850	−14.20	0.80	206.00	20	0.34
Case25	5595	−12.71	1.10	200.80	22	0.37
Case26	6050	−15.90	0.70	218.00	20	0.30
Case27	6705	−20.00	0.70	225.00	20	0.21
Case28	5400	−13.40	0.80	211.60	21	0.34
注：L_MVD为平均水滴尺寸。

下载: 导出CSV

表 2 表面温度10℃时热载荷和蒸发率结果

Table 2. Results of thermal load and evaporation rate at surface temperature of 10 ℃

编号	高度/ft	表面温度/℃	热载荷/kW	蒸发率/%
Case1	450	10	66.6	78.5
Case2	550	10	57.8	80.8
Case3	950	10	66.0	76.8
Case4	1250	10	63.6	77.8
Case5	1550	10	67.1	75.6
Case6	1850	10	63.9	76.9
Case7	2150	10	51.1	88.5
Case8	2250	10	59.1	77.7
Case9	2450	10	54.9	86.0
Case10	2450	10	66.2	74.6
Case11	2850	10	59.9	76.7
Case12	3150	10	64.1	75.4
Case13	3250	10	48.2	97.5
Case14	3450	10	61.6	75.6
Case15	3750	10	65.4	73.7
Case16	4050	10	44.9	97.5
Case17	4450	10	60.9	69.5
Case18	5250	10	64.1	97.9
Case19	5450	10	64.0	99.0
Case20	5550	10	60.8	99.5
Case21	5950	10	67.4	99.6
Case22	6050	10	64.1	99.6
Case23	6705	10	67.1	99.8
Case24	4850	10	106.2	87.7
Case25	5595	10	113.4	80.4
Case26	6050	10	106.8	91.0
Case27	6705	10	100.1	99.7
Case28	5400	10	106.9	84.7
注：上表面后缘无溢流水流出。

下载: 导出CSV

表 3 不同表面温度时的热载荷和蒸发率结果(Case3)

Table 3. Results of heatload and evaporation rate at different surface temperatures (Case3)

表面温度/℃	热载荷/kW	蒸发率/%	备注
2	27.2	63.1	上表面有少量溢流水流出
5	41.9	68.6	上表面无溢流水流出
8	56.2	73.2	上表面无溢流水流出
10	66.0	76.8	上表面无溢流水流出
12	75.9	80.8	上表面无溢流水流出
13	80.9	83.0	上表面无溢流水流出
15	91.2	87.8	上表面无溢流水流出

下载: 导出CSV

表 4 满足防冰需求的表面温度设计值

Table 4. Design value of surface temperature to meet anti-icing requirements

编号	高度/m	表面温度/℃	热载荷/kW	蒸发率/%
Case1	450	12	76.9	82.8
Case2	550	10	57.8	80.8
Case3	950	12	75.9	80.8
Case4	1250	12	73.1	81.9
Case5	1550	13	81.7	81.4
Case6	1850	12	73.1	80.8
Case7	2150	10	51.1	88.5
Case8	2250	13	71.7	83.9
Case9	2450	10	54.9	86.0
Case10	2450	13	79.9	80.2
Case11	2850	13	72.2	82.7
Case12	3150	13	76.8	80.9
Case13	3250	10	48.2	97.5
Case14	3450	13	73.7	81.2
Case15	3750	14	82.2	81.1
Case16	4050	10	44.9	97.5
Case17	4450	16	88.0	82.4
Case18	5250	8	58.2	95.8
Case19	5450	8	58.5	97.2
Case20	5550	8	56.0	99.4
Case21	5950	8	62.4	99.4
Case22	6050	8	59.3	99.6
Case23	6705	8	62.6	99.8
Case24	4850	7	87.0	81.0
Case25	5595	10	113.4	80.4
Case26	6050	7	87.8	83.6
Case27	6705	5	75.0	91.1
Case28	5400	8	94.0	80.5

下载: 导出CSV

参考文献(16)

[1]	裘燮纲, 韩凤华. 飞机防冰系统[M]. 北京: 航空专业教材编审组, 1985. QIU X G, HAN F H. Aircraft anti-icing system [M]. Beijing: Editing Group of Aviation Teaching Materials, 1985(in Chinese).
[2]	DU Y X, GUI Y W, XIAO C H, et al. Investigation on heat transfer characteristics of aircraft icing including runback water[J]. International Journal of Heat and Mass Transfer, 2010, 53(19-20): 3702-3707. doi: 10.1016/j.ijheatmasstransfer.2010.04.021
[3]	OLSEN W, SHAW R, NEWTON J. Ice shapes and the resulting drag increase for a NACA 0012 airfoil[C]//Proceedings of the 22nd Aerospace Sciences Meeting. Reston: AIAA, 1984.
[4]	CORTINAS J V Jr, BERNSTEIN B C, ROBBINS C C, et al. An analysis of freezing rain, freezing drizzle, and ice pellets across the United States and Canada: 1976–90[J]. Weather and Forecasting, 2004, 19(2): 377-390. doi: 10.1175/1520-0434(2004)019<0377:AAOFRF>2.0.CO;2
[5]	JONES S, REVELEY M, EVANS J K, et al. Subsonic aircraft safety icing study: NASA/TM-2008-215107 [R]. Washington, D. C.: NASA, 2008
[6]	郁嘉, 卜雪琴, 林贵平, 等. 非结冰气象条件下机翼热气防冰系统数值模拟[J]. 空气动力学学报, 2016, 34(5): 562-567. YU J, BU X Q, LIN G P, et al. Numerical simulation of a wing hot air anti-icing system in dry air conditions[J]. Acta Aerodynamica Sinica, 2016, 34(5): 562-567(in Chinese).
[7]	PAPADAKIS M, WONG S H, YEONG H W, et al. Icing tests of a wing model with a hot-air ice protection system[C]//Proceedings of the AIAA Atmospheric and Space Environments Conference. Reston: AIAA, 2010.
[8]	卜雪琴, 郁嘉, 林贵平, 等. 机翼热气防冰系统设计[J]. 北京航空航天大学学报, 2010, 36(8): 927-930. BU X Q, YU J, LIN G P, et al. Investigation of the design of wing hot-air anti-icing system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(8): 927-930(in Chinese).
[9]	ROSERO J A, ORTEGA J A, ALDABAS E, et al. Moving towards a more electric aircraft[J]. IEEE Aerospace and Electronic Systems Magazine, 2007, 22(3): 3-9. doi: 10.1109/MAES.2007.340500
[10]	DOMINGOS R, PAPADAKIS M, ZAMORA A. Computational methodology for bleed air ice protection system parametric analysis[C]//Proceedings of the AIAA Atmospheric and Space Environments Conference. Reston: AIAA, 2010.
[11]	倪章松, 刘森云, 张军, 等. 环境参数对飞机防冰热载荷的影响规律[J]. 航空动力学报, 2021, 36(1): 8-14. NI Z S, LIU S Y, ZHANG J, et al. Influnce of environment parameters on anti-icing heat load for aircraft[J]. Journal of Aerospace Power, 2021, 36(1): 8-14(in Chinese).
[12]	管宁. 三维机翼防冰热载荷的数值模拟[D]. 南京: 南京航空航天大学, 2007. GUAN N. Numerical simulation of anti-icing thermal loads on a 3D airfoil[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2007 (in Chinese).
[13]	卜雪琴, 郁嘉, 林贵平. 一种热气防冰系统的数值仿真[J]. 计算机仿真, 2010, 27(9): 40-43. BU X Q, YU J, LIN G P. Numerical simulation of an airfoil hot-air anti-icing system[J]. Computer Simulation, 2010, 27(9): 40-43(in Chinese).
[14]	赵勇, 杨新亮. 飞机水平尾翼水滴撞击特性及防冰热载荷计算[J]. 航空动力学报, 2012, 27(11): 2401-2407. ZHAO Y, YANG X L. Impingement characteristics and anti-icing heat load calculation of certain tailplane[J]. Journal of Aerospace Power, 2012, 27(11): 2401-2407(in Chinese).
[15]	林贵平, 卜雪琴, 申晓斌. 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, BU X Q, SHEN X B. Aircraft icing and anti-icing technology[M]. Beijing: Beijing University of Aeronautics & Astronautics Press, 2016 (in Chinese).
[16]	MESSINGER B L. Equilibrium temperature of an unheated icing surface as a function of air speed[J]. Journal of the Aeronautical Sciences, 1953, 20(1): 29-42. doi: 10.2514/8.2520