涡桨飞机发动机进气道吞鸟特性数值研究

周浩宇; 吴祯龙; 谢买祥; 谭慧俊; 郑高杰; 张峰旗; 罗刚; 陈伟

doi:10.13224/j.cnki.jasp.20230083

涡桨飞机发动机进气道吞鸟特性数值研究

doi: 10.13224/j.cnki.jasp.20230083

1.
南京航空航天大学能源与动力学院，南京 210016
2.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 民用飞机专项科研项目（MJ-2020-F-10）

详细信息

作者简介:
周浩宇（1998-），男，硕士生，主要从飞行器进气道设计和研究。E-mail：sz2102831@nuaa.edu.cn

通讯作者:
吴祯龙（1988-），男，教授、博士生导师，博士，主要从事飞行器内外流设计与研究。E-mail：zhenlongwu@nuaa.edu.cn

中图分类号: V211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2023-02-17
- 网络出版日期: 2024-03-19

Numerical simulation on bird ingestion characteristics from engine inlet of turboprop aircraft

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
根据适航规章，针对常见外来异物—鸟进行属性分析，确定其几何、质量以及初始姿态和速度特性；通过计算流体力学（CFD）将“动网格法”和六自由度方法耦合，对涡桨飞机主发动机进气道的吞鸟特性进行数值模拟，研究在螺旋桨/进气道/旁通道一体化条件下，鸟类异物被吸入发动机进气道过程中的轨迹特性与排除特性的影响规律。结果表明：鸟类异物进入进气道后会使进气道流动环境恶化，进气道气动交界面（AIP）内的总压恢复系数降低、总压畸变指数增大；在所模拟的工况下鸟都从旁通道排除或者与旁通道壁面碰撞，均可认为排除；来流马赫数对鸟进入进气道入口前的姿态有很大影响，高主流出口马赫数和大飞行攻角下鸟更容易被吸入主发动机，有可能对主发动机造成严重影响。
- 涡桨发动机 /
- 外来异物 /
- 鸟撞 /
- 进气道 /
- 旁通道
Abstract:
According to airworthiness regulations, attribute analysis on common foreign objects—birds, was conducted, and their geometric, mass, initial attitude, and velocity characteristics were determined; through computational fluid dynamics (CFD), the “dynamic grid method” and the six degrees of freedom method were coupled to numerically simulate the bird swallowing characteristics of the main engine inlet of a turboprop aircraft. The influence of the trajectory characteristics and exclusion characteristics of birds being sucked into the engine inlet was studied under the condition of integrated propeller/inlet/bypass channels. The results showed that the flow environment of the inlet may deteriorate, the total pressure coefficient of restitution in the aerodynamic interface plane (AIP) of the inlet may decrease, and the total pressure distortion may increase after the birds enter the inlet; under the simulated working conditions, birds were excluded from the side channel or collided with the wall of the side channel, which can be considered exclusion; the incoming Mach number had a significant impact on the attitude of birds before entering the inlet. At high outlet Mach numbers and high angles of attack, the bird body was more likely to be sucked into the main engine, which may have a serious impact on the main engine.
- turboprop engine /
- foreign objects /
- bird impact /
- inlet /
- bypass duct

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图 1 鸟体几何参数

Figure 1. Geometric parameters of birds

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图 2 计算模型

Figure 2. Computational model

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图 3 模型网格

Figure 3. Model grid

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图 4 进气道模型及边界条件

Figure 4. Model and boundary conditions of inlet

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图 5 壁面沿程压力分布

Figure 5. Pressure distribution along the wall

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图 6 鸟撞模型及边界条件

Figure 6. Model and boundary conditions of bird impact

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图 7 鸟轨迹测量实验

Figure 7. Bird trajectory measurement experiment

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图 8 鸟体轨迹计算结果与实验结果的比较

Figure 8. Comparison between the calculated and experimental results of bird trajectory

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图 9 鸟体模型

Figure 9. Bird model

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图 10 鹌鹑运动轨迹实验

Figure 10. Quail trajectory experiment

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图 11 鹌鹑运动速度分布

Figure 11. Quail motion velocity distribution

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图 12 鹌鹑飞行轨迹对比

Figure 12. Comparison of quail flight trajectories

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图 13 鹌鹑撞击壁面实验

Figure 13. Quail impact on wall experiment

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图 14 不同时刻进气道对称面马赫数分布

Figure 14. Mach number distribution of inlet symmetry at different times

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图 15 异物初始位置

Figure 15. Initial position of foreign object

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图 16 两种异物运动状态的比较

Figure 16. Comparison of two kinds of foreign object motion

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图 17 不同飞行攻角下进气道对称面马赫数云图

Figure 17. Mach number cloud diagram of inlet symmetry surface at different angles of attack

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图 18 不同攻角下鸟体运动轨迹

Figure 18. Motion trajectory of bird body under different angles of attack

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图 19 不同来流速度下进气道对称面马赫数分布

Figure 19. Mach number distribution on the symmetry plane of the inlet at different incoming velocities

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图 20 不同来流速度下鸟运动状态的比较

Figure 20. Comparison of bird motion state under different incoming velocities

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图 21 不同出口马赫数下进气道对称面马赫数分布

Figure 21. Mach number distribution on inlet symmetry plane at different outlet Mach numbers

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图 22 不同出口马赫数下鸟运动状态的比较

Figure 22. Comparison of bird motion at different outlet Mach numbers

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图 23 进气道入口型面

Figure 23. Inlet profile

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图 24 26°攻角下不同口面布局吞鸟轨迹

Figure 24. Inlet swallowing bird trajectories with different mouth layouts at 26° angle of attack

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图 25 28°攻角下不同口面布局吞鸟轨迹

Figure 25. Inlet swallowing bird trajectories with different mouth layouts at 28° angle of attack

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表 1 鸟体几何参数表

Table 1. Geometric parameters table of birds

类型	质量/g	L_b/mm	C/L_b	翅膀厚度/mm
小鸟	85	165.7	0.6	2

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表 2 仿真与实验主流出口性能参数对比表

Table 2. Comparison table of simulation and experimental mainstream outlet performance parameters %

参数	实验结果	仿真结果
总压恢复系数σ	97.79	98.99
总压畸变指数$\bar{D} $	4.819	6.111

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表 3 鸟类异物属性

Table 3. Bird attribute

直径/m	质量/g	转动惯量/10⁻⁸ （g·m²）
0.0192	85	I_xx=1.56672 I_yy=I_zz=4.96128

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表 4 鸟属性参数

Table 4. Bird attribute parameters

类型	质量/g	转动惯量/10⁻⁸ （g·m²）
无翅鸟	85	I_xx=6.70158 I_yy=I_zz=17.68281
有翅鸟	85	I_xx=7.80 I_yy=I_zz=180

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表 5 计算条件

Table 5. Calculation conditions

来流边界	来流马赫数Ma₀	主流出口马赫数Ma_out	螺旋桨转速/（r/min）	桨距/（°）	鸟速/（m/s）
Farfeild	0.3	0.3	920	35	80

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表 6 异物碰撞位置和进气道性能比较

Table 6. Comparison of foreign object impact location and inlet performance

类型	碰撞位置/m	AIP总压
类型	碰撞位置/m	恢复系数	畸变指数
气场		1.00658	0.0223
无翅鸟	（5.981,0.157,0.0047）	1.00648	0.0237
有翅鸟	（4.171,0.174,0.0036）	1.00616	0.0277

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表 7 不同来流速度下进气道出口性能

Table 7. Inlet outlet performance at different incoming velocities

来流马赫数	进气道总压恢复系数	进气道总压畸变指数	进气道总压恢复系数（鸟）	进气道总压畸变指数（鸟）
0	1.02318	0.028173	1.01960	0.028272
0.3	1.00658	0.022321	1.00648	0.023756
0.45	0.98801	0.030080	0.98496	0.030173

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表 8 不同出口马赫数下进气道出口性能

Table 8. Inlet outlet performance at different outlet Mach numbers

出口马赫数	进气道总压恢复系数	进气道总压畸变指数	进气道总压恢复系数（鸟）	进气道总压畸变指数（鸟）
0.2	1.01228	0.011678	1.01178	0.011684
0.3	1.00658	0.022321	1.00648	0.023756
0.45	0.99530	0.052773	0.99370	0.052858

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