高速地效条件下涡扇发动机推力性能分析

盛卓然; 孙建红; 孙智; 李佳音; 王哲

doi:10.13224/j.cnki.jasp.20250329

高速地效条件下涡扇发动机推力性能分析

doi: 10.13224/j.cnki.jasp.20250329

盛卓然^1,,
孙建红^{1, 2,*, ,},
孙智¹,
李佳音¹,
王哲²

1.
南京航空航天大学民航学院民航应急科学与技术重点实验室，南京 211106
2.
南京航空航天大学航空学院飞行器环境控制与生命保障工业和信息化部重点实验室，南京 210016

详细信息

作者简介:
盛卓然（1997-），男，博士生，主要从事地高速效飞行器飞发一体化研究。E-mail：zhusheng@nuaa.edu.cn

通讯作者:
孙建红（1968-），男，教授、博士生导师，博士，主要从事飞行器适航技术、民航应急科学与技术研究。E-mail：jhsun@nuaa.edu.cn

中图分类号: V211.3；V231.3
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出版历程
- 收稿日期: 2025-07-15
- 网络出版日期: 2025-11-30

Study on thrust performance of turbofan engine in high-speed ground effect conditions

SHENG Zhuoran^1
,,
SUN Jianhong^{1, 2,*
, ,},
SUN Zhi¹,
LI Jiayin¹,
WANG Zhe²

1.
Key Laboratory of Civil Aviation Emergency Science & Technology，College of Civil Aviation，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
2.
Key Laboratory of Aircraft Environment Control and Life Support，Ministry of Industry and Information Technology，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为研究一型高速地效飞行器机体对短舱周围流场的干扰及安装对发动机净推力的影响，对独立短舱构型和安装短舱构型的三维流场进行数值计算，采用推阻分解方法对相关推力、阻力分量进行提取，分析巡航状态下发动机安装造成的推力变化；此外对安装短舱构型，在机体轴线方向取多个发动机安装位置进行数值计算，采用推阻分解方法研究安装位置对推力的影响规律。结果表明：机翼对发动机喷流的吸附、加速使得发动机内推力及内阻分别增加0.4%及1.5%，而机体对短舱外罩表面压力分布的影响导致短舱外阻增加18.24%，是造成安装后净推力减小的主要原因；而安装位置在机体轴向的变化影响发动机的净推力，短舱越接近机翼，喷流受到的吸附、加速越强，内推力增益越明显，同时短舱外罩表面压力分布受机体干扰的影响减弱，短舱外阻降低，短舱与机翼的近耦合有利于净推力的提升，最接近机翼位置较最远离机翼位置净推力增加1.46%。
- 高速地效飞行器 /
- 飞发一体化 /
- 推阻分解 /
- 涡扇发动机 /
- 计算流体力学
Abstract:
To investigate the interference of a high-speed ground effect vehicle’s airframe on the nacelle flow field and installation effect on the net propulsive thrust, 3D numerical simulations were conducted for both isolated and installed nacelle configurations. Using thrust-drag bookkeeping method, thrust and drag components were extracted to analyse thrust changes between the two configurations in cruise conditions. Additionally, the effects of axial nacelle installation positions on net propulsive thrust were studied. Results showed that the wing’s entrainment and acceleration of the engine jet resulted in an increase of 0.4% in intrinsic net force and 1.5% in internal nacelle force, while the airframe’s influence on the nacelle cowl surface pressure distribution significantly raised external nacelle force in 18.24%, leading to net propulsive thrust reduction. Moving the nacelle closer to the wing enhanced jet entrainment and reduced external nacelle force by weakening the body interference, thus improving net propulsive thrust. The net propulsive thrust at the position closest to the wing was 1.46% higher than that at the position farthest from the wing.
- high-speed ground effect vehicle /
- engine/airframe integration /
- thrust/drag bookkeeping /
- turbofan engine /
- computational fluid dynamics

HTML

图 1 几何模型

Figure 1. Geometry model

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图 2 计算域及边界条件

Figure 2. Computational domain and boundary conditions

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图 3 两种构型计算网格

Figure 3. Computational mesh of the two configurations

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图 4 涡扇发动机推阻分解控制体

Figure 4. Thrust/drag bookkeeping control volume for a turbofan engine

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图 5 NAL-AERO-02-01 TPS短舱压力系数的计算结果

Figure 5. Comparison of the pressure coefficient of NAL-AERO-02-01 TPS nacelle

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图 6 DSFR喷管排气系数的计算结果对比

Figure 6. Comparison of the discharge coefficient of DSFR

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图 7 DSFR喷管推力系数的计算结果对比

Figure 7. Comparison of the thrust coefficient of DSFR

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图 8 净推力与机体阻力对网格尺寸敏感性曲线

Figure 8. Sensitivity of net propulsive thrust and airframe drag to the mesh size

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图 9 两种构型短舱中心面马赫数云图

Figure 9. Mach number distribution on the major section of the two nacelle configurations

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图 10 两种构型表面压力系数云图

Figure 10. Pressure coefficient distribution of the two configurations

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图 11 周向角$ \alpha $定义

Figure 11. Definition of azimuth agnle $ \alpha $

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图 12 不同周向角$ \alpha $位置的安装短舱构型与独立短舱构型压力系数曲线对比

Figure 12. Comparison of pressure coefficient curves of installed and uninstalled nacelle configurations at different azimuth agnle $ \alpha $ location

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图 13 安装位置定义

Figure 13. Definition of installation position

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图 14 推阻分解分量变化程度随安装位置曲线

Figure 14. Curve of variation degree of components of thrust/drag bookkeeping with different installation positions

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图 15 不同安装位置短舱中心面马赫数云图

Figure 15. Mach number distribution on the major section of the nacelle with different installation positions

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图 16 不同周向角$ \alpha $位置压力系数曲线对比

Figure 16. Comparison of pressure coefficient curves at different azimuth agnle $ \alpha $ location

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表 1 验证算例工况参数

Table 1. Condition parameters of the validation case

参数	数值
Ma	0.801
$ {R}_{{\mathrm{mf}}} $	0.4973
$ {R}_{{\mathrm{fp}}} $	1.3428
$ {R}_{{\mathrm{ft}}} $	1.1086
$ {R}_{{\mathrm{cp}}} $	0.9213
$ {R}_{{\mathrm{ct}}} $	0.6118

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表 2 推力配平后发动机工况

Table 2. Condition parameters of the turbofan engine with trimmed thrust

参数	数值
Ma	0.4
$ {R}_{{\mathrm{mf}}} $	0.917
$ {R}_{{\mathrm{fp}}} $	1.836
$ {R}_{{\mathrm{ft}}} $	1.453
$ {R}_{{\mathrm{cp}}} $	1.093
$ {R}_{{\mathrm{ct}}} $	1.502

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表 3 两种构型推阻分解结果

Table 3. Thrust/drag bookkeeping results of the two configurations

分量	独立短舱	安装短舱	变化/%
$ {F}_{17}/\mathrm{N} $	−61156.30	61169.06	0.02
$ {F}_{7}/\mathrm{N} $	−7385.80	−7532.22	1.98
$ {F}_{2}/\mathrm{N} $	27549.77	27544.53	−0.02
$ {\theta }_{\rm{intake}}/\mathrm{N} $	886.46	539.79	−39.11
$ {\theta }_{\rm{cone}}/\mathrm{N} $	−723.59	−725.28	0.23
$ {\varPhi }_{{\mathrm{cowl}}}/\mathrm{N} $	634.82	1128.65	77.79
$ {\theta }_{{\mathrm{bn}}}/\mathrm{N} $	5543.75	5530.81	−0.23
$ {\theta }_{{\mathrm{cn}}}/\mathrm{N} $	1633.38	1565.26	−4.17
$ {\theta }_{{\mathrm{cc}}}/\mathrm{N} $	631.89	782.40	23.82
$ {\theta }_{{\mathrm{plug}}}/\mathrm{N} $	−836.81	−802.00	−4.16
$ {F}_{{\rm{int}}}/\mathrm{N} $	40992.33	41156.75	0.40
$ {F}_{\rm{enf}}/\mathrm{N} $	797.69	943.15	18.24
$ {F}_{\rm{int}}/\mathrm{N} $	6972.21	7076.47	1.50
$ {F}_{\rm{npf}}/\mathrm{N} $	33222.43	33137.13	−0.26

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表 4 不同的安装位置

Table 4. Different installation positions

编号	位置
$ 1 $	$ （{x}_{0}-0.1{c}_{\rm{ref}},{{\textit{z}}}_{0}） $
$ 2 $	$ （{x}_{0}-0.05{c}_{\rm{ref}},{{\textit{z}}}_{0}） $
$ 3 $	$ （{x}_{0},{{\textit{z}}}_{0}） $
$ 4 $	$ （{x}_{0}+0.05{c}_{\rm{ref}},{{\textit{z}}}_{0}） $
$ 5 $	$ （{x}_{0}+0.1{c}_{\rm{ref}},{{\textit{z}}}_{0}） $

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