多通道喷管气动突片强化掺混性能的实验与数值模拟研究

陆英明; 徐惊雷; 黄帅; 潘睿丰; 董晗; 马钊

doi:10.13224/j.cnki.jasp.20250451

多通道喷管气动突片强化掺混性能的实验与数值模拟研究

doi: 10.13224/j.cnki.jasp.20250451

陆英明^1,,
徐惊雷^{1, 2},
黄帅^1,*, ,,
潘睿丰¹,
董晗¹,
马钊³

1.
南京航空航天大学能源与动力学院，南京 210016
2.
南京航空航天大学航空航天结构力学及控制全国重点实验室，南京 210016
3.
中国航发四川燃气涡轮研究院，成都 610500

基金项目: 中国博士后科学基金（2022M721598）；江苏省“卓博计划”（2022ZB214）；江苏省自然科学基金（BK20230891）；国家科技重大专项（2017-Ⅴ-0004-0054，2019-Ⅱ-0007-0027，Y2022-Ⅱ-0005-0008）；国家自然科学基金重点项目（12332018）

详细信息

作者简介:
陆英明（2001-），男，硕士生，主要研究方向为先进流动控制与流体推力矢量。E-mail：1203795832@qq.com

通讯作者:
黄帅（1992-），男，讲师，博士，主要研究方向为先进流动控制与流体推力矢量。E-mail：huangshuai0315@nuaa.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2025-09-30
- 网络出版日期: 2026-03-17

Numerical and experimental research on the performance of air tabs for mixing enhancement in multi-channel nozzles

Lu Yingming^1
,,
Xu Jinglei^{1, 2},
Huang Shuai^{1,*
, ,},
Pan Ruifeng¹,
Dong Han¹,
Ma Zhao³

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
State Key Laboratory of Mechanics and Control of Aeronautics and Astronautics Structures，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
3.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
对于广泛采用涡扇发动机的现代军用飞机，红外探测技术对飞行器的生存力构成严重的威胁。针对现代战机的高隐身性能要求，聚焦于多通道的涡扇发动机喷管，采用实验与数值模拟相结合的方法，系统探究气动突片技术的应用及其掺混性能。利用主动流动控制方法，强化多通道喷管射流的掺混，从而有效降低射流温度并抑制红外辐射，满足战机隐身性能需求。对气动突片强化掺混实验模型开展风洞实验，对比实验结果与数值模拟结果；通过实验验证的数值模拟结果表明：气动突片能够使喷管热混合效率从无突片时的约0.17提升至0.3以上，喷管下游的高温射流核心区面积减小了30%以上，且掺混几乎不引起总压和推力损失，具有良好的强化掺混效果。
- 气动突片 /
- 强化掺混 /
- 流动控制 /
- 多通道喷管 /
- 热混合效率 /
- 射流核心区面积
Abstract:
Infrared detector technologies pose a serious threat to the survivability of modern military aircraft with wide use of turbofan engines. Based on the air tab mixing enhancement technique with active flow control, experimental and numerical study was carried out on the application and mixing efficiency of air tab in multi-channel turbofan nozzle, and explored the use and control of mixing to effectively reduce the temperature of the jet to inhibit infrared radiation and meet the demand of the aircraft stealth performance. Experimental results of the model of mixing enhancement with air tab were analyzed, and verified the feasibility of the study method by comparing the experimental and numerical results. The verified numerical results show that the air tab can improve the thermal mixing efficiency of the nozzle from about 0.17 to over 0.3, and the high temperature jet core area downstream of the nozzle is reduced by more than 30%. Well mixing performance is achieved with almost no total pressure and thrust loss from mixing.
- air tab /
- mixing enhancement /
- flow control /
- multi-channel nozzle /
- thermal mixing efficiency /
- jet core area

HTML

图 1 喷管内部流道示意图

Figure 1. Flow channel of the nozzle

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图 2 喷管主体和集气室的示意及实物图

Figure 2. Diagram and figure of nozzle and gas chamber

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图 3 试验台示意图

Figure 3. Diagram of test bench

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图 4 实验模型安装图

Figure 4. Experimental model on test bench

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图 5 流场计算域及边界条件

Figure 5. Computational domain and boundary conditions

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图 6 不同密度的计算网格

Figure 6. Computational mesh with different densities

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图 7 不同网格的壁面无量纲静压分布

Figure 7. Comparison of non-dimensional wall pressure distribution for different meshes

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图 8 突片不同工作状态下数值模拟结果与实验纹影的对比

Figure 8. Comparison of numerical results and experimental schlieren pictures under different air-tab working conditions

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图 9 不同工况下数值模拟与实验结果壁面无量纲静压分布的对比

Figure 9. Comparison of numerical and experimental results of non-dimensional wall pressure distribution under different working conditions

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图 10 测压方向示意图

Figure 10. Diagram of directions of pressure measurement

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图 11 数值模拟与实验结果喷管出口无突片注射位置的径向无量纲总压分布的对比

Figure 11. Comparison of numerical and experimental results of non-dimensional radial total pressure distribution at the position without air-tab injection at nozzle exit

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图 12 数值模拟与实验结果喷管出口突片注射位置的径向无量纲总压分布的对比

Figure 12. Comparison of numerical and experimental results of non-dimensional radial total pressure distribution at the position with air-tab injection at nozzle exit

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图 13 不同工况下气动突片下游的涡量云图

Figure 13. Vorticity contours downstream of air-tab under different working conditions

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图 14 气动突片影响下喷管内温度场的变化

Figure 14. Variation of temperature contours in the nozzle under the effect of air-tab

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图 15 不同工况下喷管出口截面的温度场

Figure 15. Temperature contours at nozzle exit under different working conditions

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表 1 不同网格量下参数对比

Table 1. Comparison of parameters under different grid quantities

参数	近壁面网格y⁺	网格量/10⁴
稀疏网格	60	80
中等网格	60	200
稠密网格	60	500

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表 2 实验工况

Table 2. Working conditions of the experiment

工况	喷管主流落压比	气动突片工作状态	气动突片压比
1	2.0	关
2	2.0	开	1, 2, 3
3	2.5	关
4	2.5	开	1, 2, 3
5	3.0	关
6	3.0	开	1, 2, 3

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表 3 实验主要测量参数和测量设备

Table 3. Main measurement parameters and equipment of the experiment

测量参数	测量设备	测量范围	测量精度
内壁面沿程静压	MEAS-9216电子压力扫描阀	414 kPa/103 kPa	±0.5%
喷管径向总压分布	MEAS-9216电子压力扫描阀	414 kPa/103 kPa	±0.5%
流场纹影	Canon EOS 800D相机	4000像素×6000像素

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表 4 不同工况的掺混性能

Table 4. Mixing performance under different working conditions

主流落压比	突片压比	热混合效率	总压恢复系数	推力系数	无量纲射流核心区面积
2.0	关	0.1709	0.9338	0.9712	1.4037
	1	0.2330	0.9307	0.9723	1.2751
	2	0.2942	0.9276	0.9685	1.1579
	3	0.3198	0.9274	0.9689	0.9370
2.5	关	0.1664	0.9582	0.9728	1.5493
	1	0.2381	0.9558	0.9712	1.4646
	2	0.3174	0.9527	0.9684	1.3254
	3	0.3398	0.9512	0.9658	1.1055
3.0	关	0.2290	0.9598	0.9826	1.4275
	1	0.2683	0.9573	0.9806	1.3921
	2	0.2963	0.9555	0.9811	1.2641
	3	0.3058	0.9550	0.9780	0.9127

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