直升机防除冰系统人工结冰试验

任智勇; 李志鹏; 王俊琦; 马丁峰

doi:10.11729/syltlx20180077

直升机防除冰系统人工结冰试验

doi: 10.11729/syltlx20180077

1.
中国航空工业集团有限公司中国飞行试验研究院, 西安 710089
2.
中国人民解放军 95966部队, 哈尔滨 150060

详细信息

作者简介:
任智勇(1990-), 男, 陕西西安人, 硕士, 工程师。研究方向:气动热数值计算与工程估算, 直升机发动机飞行试验。通信地址:陕西省西安市阎良区试飞院路8号73信箱总体所(710089)。E-mail:renzy0315@126.com

通讯作者:
任智勇, E-mail: renzy0315@126.com

中图分类号: V217+.3
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- 被引次数: 0
出版历程
- 收稿日期: 2018-05-29
- 修回日期: 2019-08-14
- 刊出日期: 2019-10-25

Artificial icing tests of the helicopter anti-icing system

1.
Chinese Flight Test Establishment, Aviation Industry Corporation of China, LTD., Xi'an 710089, China
2.
The Chinese People's Liberation Army 95966 Unit, Harbin 150060, China

摘要

摘要: 为掌握结冰条件下直升机旋翼、发动机、进气道防除冰系统的性能规律，在不同液态水含量和大气温度下，开展了地面和悬停两种状态直升机人工结冰试验，研究旋翼、发动机、进气道防除冰系统在结冰环境中的相互影响。研究发现：受旋翼旋转影响，右发进气道较左发更容易结冰；发动机低功率状态下，防冰性能较差，状态升高后，防冰性能改善；旋翼结冰导致发动机状态升高，使进气道表面温度较无结冰时仍有上升。同时，旋翼上周期性的"结冰-脱除"，导致发动机参数振荡，振荡周期受环境条件影响不大，而振幅与液态水含量近似呈线性关系。
- 防除冰系统 /
- 涡轴发动机 /
- 进气道 /
- 人工结冰 /
- 飞行试验
Abstract: In order grasp the working characteristics of anti-icing systems of the helicopter rotor, the turboshaft engine and the inlet under icing conditions, the helicopter artificial icing tests were conducted. The icing tests were conducted in different liquid water contents, at different temperatures, and under both ground and hovering conditions. The interaction between the rotor, the engine and the inlet anti-icing systems was studied. It is found that the right inlet ices easier than the left side due to rotor rotating. The inlet has a poor anti-icing performance when the engine works under low power condition, and its performance improves when the engine power rises. The engine power condition rises after rotor icing, leading to a higher inlet temperature than that in the dry air. The periodical icing-shedding on the rotor results in an engine parameter fluctuation. The fluctuation period is hardly affected by the environmental condition, while the fluctuation amplitude changes linearly with the liquid water content.
- anti-icing system /
- turboshaft engine /
- inlet /
- artificial icing /
- flight test

HTML全文

图 1 直升机与结冰喷洒塔示意图

Figure 1. Sketch of helicopter and the spray tower

下载: 全尺寸图片幻灯片

图 2 左发进气道传感器位置

Figure 2. Positions of temperature transducers on left inlet

下载: 全尺寸图片幻灯片

图 3 防除冰试验状态点

Figure 3. Anti-icing experiment points

下载: 全尺寸图片幻灯片

图 4 右发参数振荡曲线

Figure 4. Curve of parameters fluctuation of the right engine

下载: 全尺寸图片幻灯片

图 5 扭矩振幅A_M与液态水含量L的关系

Figure 5. Relation of A_M and L(liquid water content)

下载: 全尺寸图片幻灯片

表 1 正向结冰试验左、右发试验结果

Table 1. Results of both engines in forward direction test

Condition	T_{45, l}/℃	T_{45, r}/℃	Q_l	Q_r	T_{t, l}/℃	T_{t, r}/℃	T_{w, l}/℃	T_{w, r}/℃
Before bleeding	b－68.1	b－81.0	-	-	-	-	d－31.2	d－32.7
After bleeding and before icing	b－31.4	b－46.3	0.945	0.941	c－1.4	c－4.8	d－2.4	d－4.1
Icing steadily	b+67.0	b+57.7	0.936	0.954	c+28.4	c+26.6	d+5.1	d－0.3

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表 2 两次结冰试验时发动机及进气道参数比较

Table 2. Comparison of engines and inlets parameters in two flight tests

No.	Condition	T₀/℃	L/(g·m^-3)	N_g/%	T₄₅/℃	M	T_t/℃	Q	T_w/℃
1	Ground fly	－18.4	1	a+0.3	b+64.0	49.8	c+29.0	0.753	d+0.3
2	Hover	－17.2	1	a+4.1	b+173.3	79.0	c+53.3	0.783	d+6.6
3	Hover without spraying	－17.2	0	a+0.8	b+110.0	56.0	c+40.2	0.873	d+4.9

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表 3 不同试验中的扭矩振幅和周期时长

Table 3. Comparison of amplitude and cycle time of different tests

T₀/℃	L/(g·m^-3)	T_c/s	A_M
－18.1	0	-	0
－20.4	0.25	Unclear	4.0
－25.1	0.25	Unclear	2.6
－13.4	0.25	74	3.8
－17.5	0.50	77	9.0
－17.0	0.50	81	8.8
－15.0	0.75	86	13.4
－18.2	0.75	84	14.4
－11.9	1.00	75	17.2
－18.4	1.00	81	22.4
－14.3	1.00	77	18.8

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参考文献(20)

[1]	Korkan K D, Dadone L, Shaw R J. Performance degradation of helicopter rotor in forward flight due to ice[J]. Journal of Aircraft, 1985, 22(8):713-718. doi: 10.2514/3.45191
[2]	Han Y Q, Palacios J. Airfoil-performance-degradation prediction based on nondimensional icing parameters[J]. AIAA Journal, 2013, 51(11):2570-2581. doi: 10.2514/1.J052207
[3]	蒋浩, 金龙, 牛上维, 等.基于合成热射流的机翼除冰实验研究[J].实验流体力学, 2017, 31(3):94-100. http://www.syltlx.com/CN/abstract/abstract11031.shtml Jiang H, Jin L, Niu S W, et al. Experimental analysis of de-icing on airfoil using heated dual synthetic jet actuators[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(3):94-100. http://www.syltlx.com/CN/abstract/abstract11031.shtml
[4]	李斯, 于雷, 金沙, 等.移动式冰风洞试验方法研究和应用[J].空气动力学学报, 2017, 35(6):855-859. doi: 10.7638/kqdlxxb-2015.0121 Li S, Yu L, Jin S, et al. Study and application of movable icing wind tunnel test method[J]. Acta Aerodynamica Sinica, 2017, 35(6):855-859. doi: 10.7638/kqdlxxb-2015.0121
[5]	KorkanK D, Cross E J Jr, Miller T L. Performance degradation of a model helicopter rotor with a generic ice shape[J]. Journal of Aircraft, 2015, 21(10):823-830. http://cn.bing.com/academic/profile?id=42e8d9e3082ee60f175957216434b962&encoded=0&v=paper_preview&mkt=zh-cn
[6]	孔满昭, 段卓毅, 马玉敏.机翼展向不同部位结冰对飞机气动力特性影响研究[J].实验流体力学, 2016, 30(2):32-37. http://www.syltlx.com/CN/abstract/abstract10914.shtml Kong M Z, Duan Z Y, Ma Y M. Study on aerodynamic characteristics of ice accretion in different wing span sections[J]. Journal of experiments in fluid mechanics, 2016, 30(2):32-37. http://www.syltlx.com/CN/abstract/abstract10914.shtml
[7]	Ahn G B, Jung K Y, Myong R S. Numerical and experimental investigation of ice accretion on rotorcraft engine air intake[J]. Journal of Aircraft, 2015, 52(3):903-909. doi: 10.2514/1.C032839
[8]	李岩, 孙策, 郭文峰, 等.利用自然低温的旋转叶片结冰风洞试验系统设计[J].实验流体力学, 2018, 32(2):40-47. http://www.syltlx.com/CN/abstract/abstract11093.shtml Li Y, Sun C, Guo W F, et al. Design of icing wind tunnel experiment system for rotating blades by using natural low temperature[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(2):40-47. http://www.syltlx.com/CN/abstract/abstract11093.shtml
[9]	Potapczuk M G. Aircraft icing research at NASA glenn research center[J]. Journal of Aerospace Engineering, 2013, 26(2):260-276. doi: 10.1061/(ASCE)AS.1943-5525.0000322
[10]	Flegel A B, Oliver M J. Preliminary results from a heavily instrumented engine ice crystal icing test in a ground based altitude test facility[R]. AIAA-2016-3894, 2016.
[11]	Hanks M L, Higgins L B, Diekmann V L. Artificial and natural icing tests production UH-60a helicopter[R]. USAAEFA-79-19, 1980.
[12]	Flemming R J, Alldridge P, Doeppner R. Artificial icing tests of the S-92A helicopter in the McKinley climatic laboratory[R]. AIAA-2004-737, 2004.
[13]	Hoff S V, Vorst J, Flemming R J, et al. Icing certification of korean utility helicopter KUH-1: artificial icing flight test[R]. AIAA-2017-3930, 2017.
[14]	Simpson M P, Render P M. Certification and operation of helicopters in icing environments[J]. Journal of Aircraft, 1998, 35(6):936-941. doi: 10.2514/2.2389
[15]	Directorate F T. Aircraft natural/artificial icing[R]. Test Operations Procedure(TOP) 7-3-537, 2009.
[16]	侯盼雪.直升机发动机进气道防冰数值仿真研究[D].北京: 北京航空航天大学, 2012. Hou P X. Numerical simulation of anti-icing system on helicopter engine inlet[D]. Beijing: Beihang university, 2012.
[17]	Drury M D, Szefi J T, Palacios J L. Full-scale testing of a centrifugally powered pneumatic de-icing system for helicopter rotor blades[J]. Journal of Aircraft, 2017, 54(1):220-228. doi: 10.2514/1.C033965
[18]	刘国强, 于琦, 董明明, 等.旋翼结冰对"黑鹰"直升机飞行性能影响分析[J].航空科学技术, 2013(1):34-37. doi: 10.3969/j.issn.1007-5453.2013.01.010 Liu G Q, Yu Q, Dong M M, et al. The influence of rotor icing to the flight performance of black hawk helicopter[J]. Aeronautical Science and Technology, 2013(1):34-37. doi: 10.3969/j.issn.1007-5453.2013.01.010
[19]	Kreeger R E, Douglass R, Gazella M, et al. Analysis and prediction of ice shedding for a full-scale heated tail rotor[R]. AIAA-2016-3443, 2016.
[20]	Bain J, Cajigas J, Sankar L, et al. Prediction of rotor blade ice shedding using empirical methods[R]. AIAA-2010-7985, 2010.