某桨扇发动机舱通风引射排气特性仿真研究

王怡宁; 季佳圆; 章欣涛; 陈俊; 李挺

doi:10.13224/j.cnki.jasp.20240555

某桨扇发动机舱通风引射排气特性仿真研究

doi: 10.13224/j.cnki.jasp.20240555

王怡宁^{1, 3, 4,},
季佳圆²,
章欣涛²,
陈俊²,
李挺^{1, 3, 4,*, ,}

1.
北京航空航天大学能源与动力工程学院，北京 100191
2.
中国航发商用航空发动机有限责任公司，上海 200241
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 100191
4.
先进航空发动机协同创新中心，北京 100191

基金项目: 中央高校基本科研业务费专项资金资助（501XTCX2023146001）

详细信息

作者简介:
王怡宁（1999-），男，硕士，主要从事短舱通风冷却等研究。E-mail：wyn2018ysu@163.com

通讯作者:
李挺（1981-），男，副教授、博士生导师，博士，从事发动机激光燃烧诊断等研究。E-mail：li1329@buaa.edu.cn

中图分类号: V231.3
计量
- 文章访问数: 333
- HTML浏览量: 131
- PDF量: 32
- 被引次数: 0
出版历程
- 收稿日期: 2024-08-07
- 网络出版日期: 2026-02-13

CFD-based research on exhaust characteristics of ejector for propfan engine nacelle ventilating

WANG Yining^{1, 3, 4
,},
JI Jiayuan²,
ZHANG Xintao²,
CHEN Jun²,
LI Ting^{1, 3, 4,*
, ,}

1.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
2.
Commercial Aircraft Engine Company Limited，Aero Engine corporation of China，Shanghai 200241，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Thermodynamics，Beihang University，Beijing 100191，China
4.
Collaborative Innovation Center for Advanced Aero-Engine，Beijing 100191，China

摘要

摘要:
为分析某桨扇发动机构型低空低速工况下引射通风结构对排气流动性能的影响，构建了核心机舱/内涵喷管/引射次流出口一体的仿真物理模型，采用数值模拟方法对多种引射结构方案对排气特性的影响进行了研究，并从流动机理的角度对引起变化的原因进行了分析。结果表明：低空低速工况下次流流量系数随着引射出口长度比增大而减小，后趋势平缓，随开度比D₂/D₁减小到一定值附近出现峰值。掺混点（主次流边界速度一致点）的状态可标志主次流边界混合均匀；主流对次流的抽吸能力随引射出口长度比减小而增大，至长度比L₁/D₁为0.66附近时达到最大；随着马赫数从0.01增大到0.2，次流换算流量比在各马赫数下增长变化趋势相似，各型面流量系数均高于低来流马赫数方案，证明了全飞行包线下低空低速工况整机通风情况的严峻性。最后提出了流量系数与长度比及开度比的经验关系式拟合模型。
- 桨扇发动机 /
- 引射排气 /
- 通风设计 /
- 流量系数 /
- 拟合模型
Abstract:
In order to analyze the influence of ejection ventilation structure on exhaust flow performance under low altitude and low speed conditions of a propfan engine configuration, a simulation model incorporating core compartment/internal nozzle/ejection outlet was constructed. The influence of various ejection structure schemes on exhaust characteristics was researched by numerical simulation method, and the causes for the change were analyzed from the perspective of flow mechanism. The results show that the secondary flow coefficient decreases with the increase of the length ratio of the ejector outlet under low-altitude and low-speed conditions, and the trend is gentle later, simultaneously the peak appears near a certain value with the decrease of the opening ratio D₂/D₁. The state of the mixing point (the uniform point of the boundary velocity of the primary and secondary flow) can indicate the uniform mixing of the boundary layer of primary and secondary flow. The pumping capacity of the mainstream to the secondary flow increases with the decrease of the length ratio of the ejector outlet, and reaches the maximum when the length ratio L₁/D₁ is near 0.66. With the increase of Mach number from 0.01 to 0.2, the trend of the conversion flow ratio at each Mach number is similar, and the flow coefficient of each profile is higher than that of the low-flow Mach number scheme, which proves the severity of the ventilation of the engine under the low-altitude and low-speed conditions under the flight envelope. Finally, an empirical correlation fitting model between flow coefficient and length ratio and opening ratio is proposed.
- propfan engine /
- ejecting exhaust /
- ventilation design /
- flow coefficient /
- fitting model

HTML

图 1 某开式转子桨扇发动机气动布局

Figure 1. Aerodynamic layout of an open-rotor propfan engine

下载: 全尺寸图片幻灯片

图 2 各引射排气方案设计示意图

Figure 2. Schematic diagram of each ejector exhaust scheme design

下载: 全尺寸图片幻灯片

图 3 三维计算模型

Figure 3. 3D computational model

下载: 全尺寸图片幻灯片

图 4 二维与三维计算结果对比

Figure 4. Comparison of 2D and 3D calculation results

下载: 全尺寸图片幻灯片

图 5 二维模型网格局部

Figure 5. Local grid of 2D model

下载: 全尺寸图片幻灯片

图 6 网格独立性验证

Figure 6. Grid independence verification

下载: 全尺寸图片幻灯片

图 7 某桨扇发动机通风引射流路及边界条件

Figure 7. Ventilation jet path and boundary conditions of the propfan engine

下载: 全尺寸图片幻灯片

图 8 亚临界状态内涵静压分布

Figure 8. Connotation static pressure distribution in subsonic state

下载: 全尺寸图片幻灯片

图 9 轴对称计算仿真结果

Figure 9. Axisymmetric numerical simulation results

下载: 全尺寸图片幻灯片

图 10 45°倾斜排气口流量系数特性曲线

Figure 10. Flow coefficient characteristic curve of 45° inclined vent-out

下载: 全尺寸图片幻灯片

图 11 流量系数随引射出口长度比变化分布

Figure 11. Distribution of flow coefficient with ejection outlet length ratio

下载: 全尺寸图片幻灯片

图 12 次流出口局部流场速度矢量变化

Figure 12. Local flow field velocity vector change of secondary flow outlet

下载: 全尺寸图片幻灯片

图 13 主次流径向截面流速分布

Figure 13. Radial section velocity distribution of primary and secondary flow

下载: 全尺寸图片幻灯片

图 14 混合流总压随次流出口长度比分布

Figure 14. Distribution of total pressure of mixed flow with secondary flow outlet length ratio

下载: 全尺寸图片幻灯片

图 15 抽吸系数随引射出口长度比变化分布

Figure 15. Distribution of suction coefficient with ejection outlet length ratio

下载: 全尺寸图片幻灯片

图 16 D₂/D₁=0.211时次流出口局部流场分布

Figure 16. Local flow field distribution of secondary flow when D₂/D₁=0.211

下载: 全尺寸图片幻灯片

图 17 次流出口局部流场分布

Figure 17. Local flow field distribution of secondary flow

下载: 全尺寸图片幻灯片

图 18 D₂/D₁=0.063时产生的局部回流区（图17（c）中B处局部放大）

Figure 18. Local recirculation zone generated when D₂/D₁=0.063 （Local amplification at B in Fig. 17（c））

下载: 全尺寸图片幻灯片

图 19 流量系数随引射出口开度比变化分布

Figure 19. Distribution of flow coefficient with ejection outlet opening ratio

下载: 全尺寸图片幻灯片

图 20 抽吸系数随引射出口开度比变化分布

Figure 20. Distribution of suction coefficient with ejection outlet opening ratio

下载: 全尺寸图片幻灯片

图 21 D₂/D₁=0.147时次流换算流量比随不同来流马赫数变化分布

Figure 21. Distribution of the conversion flow rate of secondary flow with inflow Mach numbers when D₂/D₁=0.147

下载: 全尺寸图片幻灯片

图 22 流量系数拟合云图

Figure 22. Contour of the flow coefficient

下载: 全尺寸图片幻灯片

图 23 拟合曲面与仿真数据对比

Figure 23. Comparison of fitting surface and simulation data

下载: 全尺寸图片幻灯片

表 1 各方案主要特征几何参数

Table 1. Main geometric parameters of each scheme

方案	D₂/D₁				L₁/D₁
方案	x=1	x=2	x=3	x=4	L₁/D₁
Casex-1	0.211	0.147	0.103	0.063	0.56
Casex-2	0.211	0.147	0.103	0.063	0.66
Casex-3	0.211	0.147	0.103	0.063	0.77
Casex-4	0.211	0.147	0.103	0.063	0.97

下载: 导出CSV

表 2 计算工况表

Table 2. Table of calculation condition

方案	计算工况
方案	Ma
Case1	0.01	0.05	0.1	0.2	0.3
Case2-1	0.01	0.05	0.1	0.2
Case2-2	0.01	0.05	0.1	0.2	0.3
Case2-3		0.05	0.1	0.2
Case2-4	0.01	0.05	0.1	0.2
Case3-1	0.01	0.05	0.1	0.2
Case3-2	0.01	0.05	0.1	0.2	0.3
Case3-3	0.01	0.05	0.1	0.2
Case3-3	0.01	0.05	0.1	0.2
Case4-1		0.05	0.1	0.2
Case4-2	0.01	0.05	0.1	0.2	0.3
Case4-3		0.05	0.1	0.2
Case4-3	0.01	0.05	0.1	0.2

下载: 导出CSV

表 3 拟合常数表

Table 3. Table of fitting constants

拟合常数	Ma =0.05	Ma =0.1	Ma =0.2
a	1.90	1.58	1.74
b	−0.46	−0.39	−0.37
c	0.07	0.05	0.02
d	−0.29	−0.16	−0.18
e	−0.23	−0.29	−0.14
f	0.35	0.44	0.37
g	−0.51	−0.43	−0.42

下载: 导出CSV

表 4 误差分析表

Table 4. Table of error analysis

Ma	调整相关系数	误差平方和（SSE）
0.05	0.88	0.000446
0.1	0.88	0.000195
0.2	0.90	0.000128

下载: 导出CSV

参考文献(26)

[1]	黄兴, 李伟, 杨宇飞, 等. 桨扇发动机推进效率分析方法研究[J]. 航空工程进展, 2024, 15(4): 50-55. HUANG Xing, LI Wei, YANG Yufei, et al. Research on analysis method of propulsive efficiency of prop-fan engine[J]. Advances in Aeronautical Science and Engineering, 2024, 15(4): 50-55. (in Chinese HUANG Xing, LI Wei, YANG Yufei, et al. Research on analysis method of propulsive efficiency of prop-fan engine[J]. Advances in Aeronautical Science and Engineering, 2024, 15(4): 50-55. (in Chinese)
[2]	周莉, 是介, 王占学. 开式转子发动机研究进展[J]. 推进技术, 2019, 40(9): 1921-1932. ZHOU Li, SHI Jie, WANG Zhanxue. Research progress in open rotor engine[J]. Journal of Propulsion Technology, 2019, 40(9): 1921-1932. (in Chinese ZHOU Li, SHI Jie, WANG Zhanxue. Research progress in open rotor engine[J]. Journal of Propulsion Technology, 2019, 40(9): 1921-1932. (in Chinese)
[3]	PAN Chengxiong, ZHANG Jingzhou, SHAN Yong. Effects of exhaust temperature on helicopter infrared signature[J]. Applied Thermal Engineering, 2013, 51(1/2): 529-538. doi: 10.1016/j.applthermaleng.2012.09.016
[4]	PAN Chengxiong, ZHANG Jingzhou, REN Lifeng, et al. Effects of rotor downwash on exhaust plume flow and helicopter infrared signature[J]. Applied Thermal Engineering, 2014, 65(1/2): 135-149. doi: 10.1016/j.applthermaleng.2014.01.009
[5]	张志伟, 马松, 陈雪芳, 等. 收敛喷管的引射效应对背负式短舱温度影响研究[J]. 飞机设计, 2014, 34(6): 1-6. ZHANG Zhiwei, MA Song, CHEN Xuefang, et al. Research on the influence of convergent nozzle ejector effect on top-mounted nacelle of the temperature field[J]. Aircraft Design, 2014, 34(6): 1-6. (in Chinese ZHANG Zhiwei, MA Song, CHEN Xuefang, et al. Research on the influence of convergent nozzle ejector effect on top-mounted nacelle of the temperature field[J]. Aircraft Design, 2014, 34(6): 1-6. (in Chinese)
[6]	ZHANG Jingyang, GENG Jinxin, YANG Sen, et al. Influence of geometric parameters on the performance of ejector used in aeroengine air system[J]. Thermal Science and Engineering Progress, 2023, 37: 101571. doi: 10.1016/j.tsep.2022.101571
[7]	王广振, 吴寿生, 王之珊, 等. 混合管面积和位置对排气引射器性能的影响[J]. 推进技术, 2000, 21(4): 20-23. WANG Guangzhen, WU Shousheng, WANG Zhishan, et al. Effect of mixing tube area and position on performances for lobed ejector[J]. Journal of Propulsion Technology, 2000, 21(4): 20-23. (in Chinese WANG Guangzhen, WU Shousheng, WANG Zhishan, et al. Effect of mixing tube area and position on performances for lobed ejector[J]. Journal of Propulsion Technology, 2000, 21(4): 20-23. (in Chinese)
[8]	饶珠明, 王兵. 微型涡喷发动机引射特性研究[J]. 弹箭与制导学报, 2017, 37(4): 106-108, 127. RAO Zhuming, WANG Bing. Study on ejection performance of micro-turbojet engine[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017, 37(4): 106-108, 127. (in Chinese doi: 10.15892/j.cnki.djzdxb.2017.04.025 RAO Zhuming, WANG Bing. Study on ejection performance of micro-turbojet engine[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017, 37(4): 106-108, 127. (in Chinese) doi: 10.15892/j.cnki.djzdxb.2017.04.025
[9]	叶宇琛. 直升机排气引射器配合角度对引射性能的影响[J]. 中国科技信息, 2020(6): 24-27. YE Yuchen. Influence of matching angle of helicopter exhaust ejector on ejector performance[J]. China Science and Technology Information, 2020(6): 24-27. (in Chinese doi: 10.3969/j.issn.1001-8972.2020.06.005 YE Yuchen. Influence of matching angle of helicopter exhaust ejector on ejector performance[J]. China Science and Technology Information, 2020(6): 24-27. (in Chinese) doi: 10.3969/j.issn.1001-8972.2020.06.005
[10]	钱尧一, 侯亮, 卜祥建, 等. 发动机舱排气引射系统多目标优化设计[J]. 工程机械, 2014, 45(1): 40-45, 120. QIAN Yaoyi, HOU Liang, BU Xiangjian, et al. Multi-objective optimal design of underhood exhaust ejector system in engine compartment[J]. Construction Machinery and Equipment, 2014, 45(1): 40-45, 120. (in Chinese QIAN Yaoyi, HOU Liang, BU Xiangjian, et al. Multi-objective optimal design of underhood exhaust ejector system in engine compartment[J]. Construction Machinery and Equipment, 2014, 45(1): 40-45, 120. (in Chinese)
[11]	马帅, 王晓雨. 引射器数值模拟与关键结构参数优化设计[J]. 机械工程与自动化, 2024, 53(4): 55-57. MA Shuai, WANG Xiaoyu. Numerical simulation and key structural parameter optimization design of ejector[J]. Mechanical Engineering & Automation, 2024, 53(4): 55-57. (in Chinese doi: 10.3969/j.issn.1672-6413.2024.04.019 MA Shuai, WANG Xiaoyu. Numerical simulation and key structural parameter optimization design of ejector[J]. Mechanical Engineering & Automation, 2024, 53(4): 55-57. (in Chinese) doi: 10.3969/j.issn.1672-6413.2024.04.019
[12]	骆广琦, 李游, 刘琨, 等. 变循环发动机组合变几何调节方案[J]. 航空动力学报, 2014, 29(10): 2273-2278. LUO Guangqi, LI You, LIU Kun, et al. Combined variable geometry regulation schemes for variable cycle engine[J]. Journal of Aerospace Power, 2014, 29(10): 2273-2278. (in Chinese doi: 10.13224/j.cnki.jasp.2014.10.001 LUO Guangqi, LI You, LIU Kun, et al. Combined variable geometry regulation schemes for variable cycle engine[J]. Journal of Aerospace Power, 2014, 29(10): 2273-2278. (in Chinese) doi: 10.13224/j.cnki.jasp.2014.10.001
[13]	窦健, 吴琼. 变循环发动机后涵道引射器调节工况的数值研究[J]. 机械制造与自动化, 2020, 49(3): 195-197. DOU Jian, WU Qiong. Research on operating characteristics of rear variable area bypass circular injector of variable cycle engine[J]. Machine Building & Automation, 2020, 49(3): 195-197. (in Chinese doi: 10.19344/j.cnki.issn1671-5276.2020.03.052 DOU Jian, WU Qiong. Research on operating characteristics of rear variable area bypass circular injector of variable cycle engine[J]. Machine Building & Automation, 2020, 49(3): 195-197. (in Chinese) doi: 10.19344/j.cnki.issn1671-5276.2020.03.052
[14]	窦健, 汪明生, 吴琼. 变循环发动机后可变面积环形涵道引射器工作特性研究[C]//第八届中国航空学会青年科技论坛论文集. 广东江门: 中国航空学会, 2018: 168-174. DOU Jian, WANG Mingsheng, WU Qiong. Research on operating characteristics of rear variable bypass circular injector of variable cyc engine[C]//8th Youth Technology 8th Youth Technology Conference of Chinese Aerospace Society Arcticles Collection. Jiangmen Guangdong: Chinese Aerospace Society, 2018: 168-174(in Chinese DOU Jian, WANG Mingsheng, WU Qiong. Research on operating characteristics of rear variable bypass circular injector of variable cyc engine[C]//8th Youth Technology 8th Youth Technology Conference of Chinese Aerospace Society Arcticles Collection. Jiangmen Guangdong: Chinese Aerospace Society, 2018: 168-174(in Chinese)
[15]	LINEBERRY D, LANDRUM B. Effects of multiple nozzles on asymmetric ejector performance[R]. AIAA-2005-4283, 2005.
[16]	LIU Huadong, DANG Hao, JIN Zhaoyang, et al. Effects of the nozzle throat diameter on a bi-evaporator compression/ejection refrigeration system[J]. Heat and Mass Transfer, 2022, 58(12): 2207-2219. doi: 10.1007/s00231-022-03205-2
[17]	袁建新, 余建祖, 王先炜, 等. 基于旋翼下洗流场的直升机动力舱通风冷却系统仿真[J]. 直升机技术, 2009(1): 31-36. YUAN Jianxin, YU Jianzu, WANG Xianwei, et al. Simulation study of helicopter nacelle ventilation cooling system considering of downwash flow[J]. Helicopter Technique, 2009(1): 31-36. (in Chinese doi: 10.3969/j.issn.1673-1220.2009.01.007 YUAN Jianxin, YU Jianzu, WANG Xianwei, et al. Simulation study of helicopter nacelle ventilation cooling system considering of downwash flow[J]. Helicopter Technique, 2009(1): 31-36. (in Chinese) doi: 10.3969/j.issn.1673-1220.2009.01.007
[18]	张镜洋, 吴聪慧, 成锋娜, 等. 流动参数对发动机冷却用引射器性能的影响[J]. 航空动力学报, 2021, 36(5): 977-986. ZHANG Jingyang, WU Conghui, CHENG Fengna, et al. Effect of flow parameters on ejection performance of ejector for engine cooling[J]. Journal of Aerospace Power, 2021, 36(5): 977-986. (in Chinese doi: 10.13224/j.cnki.jasp.2021.05.009 ZHANG Jingyang, WU Conghui, CHENG Fengna, et al. Effect of flow parameters on ejection performance of ejector for engine cooling[J]. Journal of Aerospace Power, 2021, 36(5): 977-986. (in Chinese) doi: 10.13224/j.cnki.jasp.2021.05.009
[19]	孙顺利, 李纲, 芦海洋, 等. 主动引射自由射流试验系统舱压的仿真建模分析[J]. 推进技术, 2022, 43(5): 200994. SUN Shunli, LI Gang, LU Haiyang, et al. Modeling analysis on vacuum pressure of a free jet test system with active ejector[J]. Journal of Propulsion Technology, 2022, 43(5): 200994. (in Chinese doi: 10.13675/j.cnki.tjjs.200994 SUN Shunli, LI Gang, LU Haiyang, et al. Modeling analysis on vacuum pressure of a free jet test system with active ejector[J]. Journal of Propulsion Technology, 2022, 43(5): 200994. (in Chinese) doi: 10.13675/j.cnki.tjjs.200994
[20]	CONNER D, EDWARDS B, KLEIN P, et al. NASA/Army/Bell XV-15 tiltrotor low noise terminal area operations flight research program[R]. AIAA-2000-1923, 2000.
[21]	TAI T. Simulation and analysis of V-22 tiltrotor aircraft forward flight flowfield[R]. AIAA-1995-45, 1995.
[22]	陈尧, 单勇, 张靖周. 涡桨发动机舱引射通风冷却数值研究[J]. 航空计算技术, 2024, 54(1): 76-81. CHEN Yao, SHAN Yong, ZHANG Jingzhou. Numerical study on exhaust ejection and nacelle cooling of turboprop engine[J]. Aeronautical Computing Technique, 2024, 54(1): 76-81. (in Chinese CHEN Yao, SHAN Yong, ZHANG Jingzhou. Numerical study on exhaust ejection and nacelle cooling of turboprop engine[J]. Aeronautical Computing Technique, 2024, 54(1): 76-81. (in Chinese)
[23]	DEWEY P E, VICK A R. An investigation of the discharge and drag characteristics of auxiliary-air outlets discharging into a transonic stream[R]. NACA-TN-3466, 1955.
[24]	环夏, 杨青真, 高翔, 等. 大涵道比涡扇发动机分开式排气系统设计参数影响研究[J]. 航空工程进展, 2013, 4(2): 211-218. HUAN Xia, YANG Qingzhen, GAO Xiang, et al. Numerical investigation into the effect of design parameters on high bypass ratio separate flow exhaust system performance[J]. Advances in Aeronautical Science and Engineering, 2013, 4(2): 211-218. (in Chinese doi: 10.3969/j.issn.1674-8190.2013.02.013 HUAN Xia, YANG Qingzhen, GAO Xiang, et al. Numerical investigation into the effect of design parameters on high bypass ratio separate flow exhaust system performance[J]. Advances in Aeronautical Science and Engineering, 2013, 4(2): 211-218. (in Chinese) doi: 10.3969/j.issn.1674-8190.2013.02.013
[25]	陈灿平, 李漫露, 田晓沛. 分开式排气系统气动性能与喷流特性数值研究[J]. 航空发动机, 2017, 43(2): 23-30. CHEN Canping, LI Manlu, TIAN Xiaopei. CFD-based research on aerodynamic performance of separate-flow exhaust system of high bypass ratio turbofan engine[J]. Aeroengine, 2017, 43(2): 23-30. (in Chinese doi: 10.13477/j.cnki.aeroengine.2017.02.005 CHEN Canping, LI Manlu, TIAN Xiaopei. CFD-based research on aerodynamic performance of separate-flow exhaust system of high bypass ratio turbofan engine[J]. Aeroengine, 2017, 43(2): 23-30. (in Chinese) doi: 10.13477/j.cnki.aeroengine.2017.02.005
[26]	邓文剑, 代瑛, 王家启. 引射喷管流量及推力特性数值研究[J]. 航空科学技术, 2014, 25(6): 9-13. DENG Wenjian, DAI Ying, WANG Jiaqi. Numerical investigation on mass-flow and thrust performance of the ejector-nozzle[J]. Aeronautical Science & Technology, 2014, 25(6): 9-13. (in Chinese DENG Wenjian, DAI Ying, WANG Jiaqi. Numerical investigation on mass-flow and thrust performance of the ejector-nozzle[J]. Aeronautical Science & Technology, 2014, 25(6): 9-13. (in Chinese)