基于适航符合性的短舱风扇一体化迎角与侧风特性

傅文广; 郭重佳; 孙鹏; 陶立权

doi:10.13224/j.cnki.jasp.20220180

基于适航符合性的短舱风扇一体化迎角与侧风特性

doi: 10.13224/j.cnki.jasp.20220180

傅文广¹,
郭重佳²,
孙鹏^1,*, ,,
陶立权¹

1.
中国民航大学安全科学与工程学院，天津 300300
2.
大连海事大学轮机工程学院，辽宁大连 116026

基金项目: 天津市多元投入基金项目青年项目（21JCQNJC00930）

详细信息

作者简介:
傅文广（1989-），男，讲师，博士，主要从事航空发动机气动热力学及适航技术研究

通讯作者:
孙鹏（1979-），男，教授、博士生导师，博士，主要从事航空发动机气动热力学与适航技术研究。E-mail：sp_hit@hotmail.com

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-31
- 网络出版日期: 2023-11-01

Integrated attack angle and crosswind characteristics of nacelle-and-fan based on airworthiness compliance

1.
College of Safety Science and Engineering，Civil Aviation University of China，Tianjin 300300，China
2.
Marine Engineering College，Dalian Maritime University，Dalian Liaoning 116026，China

摘要

摘要:
以某小型涡扇发动机为研究对象，采用数值模拟方法对0°、15°、25°迎角和±10、±20、±30 m/s的90°横向侧风条件下短舱风扇一体化的特性及流场进行研究。结果表明：随着迎角的增大，相同风速条件下逆向侧风对短舱进气道和风扇性能的负面影响更大，依据机动性、风速和喘振/失速特性的适航条款要求，得到迎角为25°时，短舱风扇一体化性能可承受的正、逆向侧风范围分别约为0～23 m/s和0～18 m/s，相应得到侧风速度为±30 m/s时，所允许的机动迎角范围分别约为0°～3°和0°～2°。
- 进气畸变 /
- 喘振/失速 /
- 短舱进气道 /
- 风扇 /
- 适航符合性
Abstract:
By taking turbofan engine as the research object, the characteristics and flow field of nacelle and fan integration under the conditions of 0°, 15°, 25° attack angle and 90° crosswind of ±10, ±20 m/s and ±30 m/s were studied by numerical simulation. The results showed that with the increase of attack angle, the negative effect of the reverse crosswind on the performance of the nacelle inlet and fan was greater under the same wind speed. According to the airworthiness clause requirements of maneuverability, wind speed and surge/stall characteristics, when the attack angle was 25°, the forward and reverse crosswind ranges that the nacelle and fan integration performance can withstand were about 0−23 m/s and 0−18 m/s, respectively, and when the crosswind speed was ±30 m/s, the allowable maneuvering attack angle ranges were about 0°−3° and 0°−2°, respectively.
- inlet distortion /
- surge/stall /
- nacelle inlet /
- fan /
- airworthiness compliance

HTML

图 1 发动机物理模型

Figure 1. Engine structure physical model

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图 2 计算网格

Figure 2. Computational grid

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图 3 网格无关性验证

Figure 3. Grid independence verification

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图 4 边界条件

Figure 4. Boundary conditions

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图 5 来流与侧风方向示意图

Figure 5. Schematic diagram of incoming flow and crosswind direction

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图 6 进气道壁面压力数值校核结果

Figure 6. Numerical verification results of inlet wall pressure

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图 7 风扇特性数值校核结果

Figure 7. Numerical verification results of fan characteristics

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图 8 进气道总压恢复系数特性

Figure 8. Characteristics of total pressure recovery coefficient of inlet

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图 9 AIP总压恢复系数云图

Figure 9. Total pressure coefficient contour of AIP

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图 10 风扇进口极限流线与速度流线

Figure 10. Fan inlet limit streamline and speed streamline

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图 11 风扇效率和压比特性（Ma=0.4）

Figure 11. Characteristics of fan efficiency and pressure ratio （Ma=0.4）

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图 12 风扇喘振裕度特性

Figure 12. Fan surge margin characteristics

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图 13 风扇99%叶高S₁流面熵和相对马赫数分布

Figure 13. Entropy and relative Mach number distribution of fan 99% blade height S₁ flow surface

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图 14 近失速工况风扇99%叶高S₁流面相对马赫数和速度流线

Figure 14. Relative Mach number and velocity streamline of fan 99% blade height S₁ flow surface near stall

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图 15 OGV总压损失系数沿叶高变化曲线

Figure 15. Variation curve of OGV total pressure loss coefficient along blade height

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图 16 OGV吸力面极限流线及出口密流（AOA为25°）

Figure 16. OGV suction surface limit streamline and outlet dense flow （AOA of 25°）

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表 1 风扇与OGV设计参数

Table 1. Design parameters of fan and OGV

设计参数数值

风扇数 14

转速/（r/min） 13069

风扇叶顶间隙 0.5

风扇展弦比 1.46

OGV数 40

总增压比 1.19

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