变循环发动机变几何特性分析及其匹配优化

李峰; 伊卫林

doi:10.13224/j.cnki.jasp.20250082

变循环发动机变几何特性分析及其匹配优化

doi: 10.13224/j.cnki.jasp.20250082

李峰,
伊卫林^*, ,

北京理工大学机械与车辆学院，北京 100081

基金项目: 国家自然科学基金面上项目（52176035）

详细信息

作者简介:
李峰（2002-），男，硕士生，主要从事涡轮基发动机总体循环性能仿真的研究。E-mail：3120240474@bit.edu.cn

通讯作者:
伊卫林（1978-），男，副教授，博士，主要从事航发/燃机气动热力学的研究。E-mail：yiweilin@bit.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2025-02-20
- 网络出版日期: 2025-11-19

Analysis of variable geometry characteristics and matching optimization of variable cycle engine

LI Feng,
YI Weilin^{*
, ,}

School of Mechanical and Engineering，Beijing Institute of Technology，Beijing 100081，China

摘要

摘要:
开发了适于变循环发动机建模的部件级模型，搭建了双外涵VCE仿真模型，分析了变几何部件耦合调控机制及其对发动机性能的影响。通过建立双外涵VCE模型并与常规涡扇发动机（F135-PW-100）对比，验证了模型的精度，并基于变几何影响特性进行了整机性能匹配优化。研究表明：调节前/后可变面积涵道引射器（F/RVABI）可改变涵道比，RVABI向外涵调节可提高推力2.1%；模式选择阀（MSV）关闭时，单位推力提高6.8%；核心驱动风扇级（CDFS）导叶调节可改善喘振裕度但优化效果有限；风扇、低压涡轮与喷管的联合调节下，双外涵状态的推力可以提高5.75%。
- 变循环发动机 /
- 部件级模型 /
- 总体性能 /
- 性能优化 /
- 变几何调节
Abstract:
A component-level model suitable for variable cycle engines (VCE) was developed, and a dual-bypass VCE simulation model was established to analyze the coupled regulation mechanisms of variable geometry components and their impact on engine performance. The dual-bypass VCE model was validated against a conventional turbofan engine (F135-PW-100), and the overall performance matching optimization was carried out based on the influence characteristics of variable geometry. The results showed that adjusting the front/rear variable area bypass injectors (F/RVABI) can modify the bypass ratio, with RVABI adjustment towards the outer bypass increasing the thrust by 2.1%. Closing the mode selection valve (MSV) increased specific thrust by 6.8%. Core-driven fan stage (CDFS) vane adjustment improved stall margin but had limited optimization effects. Under the combined adjustment of the fan, low pressure turbine, and nozzle, the thrust in the dual-bypass mode can be increased by 5.75%.
- variable cycle engine /
- component-level model /
- overall performance /
- performance optimization /
- variable geometry adjust

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图 1 基于部件级模型的航空发动机建模过程

Figure 1. Process of modeling based on component-level models for aircraft engines

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图 2 VCE结构示意

Figure 2. Structural diagram of VCE

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图 3 MSV结构示意

Figure 3. Structural diagram of MSV

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图 4 MSV模型示意图

Figure 4. Model diagram of MSV

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图 5 VABI结构示意

Figure 5. Structural diagram of VABI

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图 6 VABI简化模型

Figure 6. Simplified model of VABI

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图 7 VABI求解逻辑

Figure 7. Solution logic diagram of VABI

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图 8 VABI模型示意图

Figure 8. Model diagram of VABI

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图 9 F135结构示意^[20]

Figure 9. Structural diagram of F135^[20]

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图 10 推力与α_RVABI的曲线

Figure 10. Curves of thrust and α_RVABI

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图 11 单位推力与α_RVABI曲线

Figure 11. Curves of specific thrust and α_RVABI

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图 12 质量流量与α_RVABI的曲线

Figure 12. Curves of mass flow and α_RVABI

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图 13 涵道比与α_RVABI的曲线

Figure 13. Curves of bypass ratio and α_RVABI

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图 14 推力与α_CDFS的曲线

Figure 14. Curves of thrust and α_CDFS

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图 15 单位推力与α_CDFS的曲线

Figure 15. Curves of specific thrust and α_CDFS

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图 16 推力与α_fan曲线

Figure 16. Curves of thrust and α_fan

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图 17 单位推力与α_fan的曲线

Figure 17. Curves of specific thrust and α_fan

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图 18 风扇工作线

Figure 18. Operating lines of fan

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图 19 高压压气机工作线

Figure 19. Operating lines of high pressure compressor

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图 20 推力与的α_fan曲线

Figure 20. Curves of thrust and α_fan

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图 21 单位推力与α_fan的曲线

Figure 21. Curves of specific thrust and α_fan

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图 22 推力与喷管开度的曲线

Figure 22. Curves of thrust and nozzle ratio

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图 23 推力随低压涡轮导向器开度、喷管开度与α_fan的响应面

Figure 23. Response surface of thurst affected by low pressure turbine ratio，nozzle ratio and α_fan

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表 1 F135总体性能参数

Table 1. Overall performance parameters of F135

参数	数值
质量流量/（kg/s）	147
涵道比	0.57
进气道压力损失系数	0.1
风扇压比	4.7
风扇效率	0.9
高压压气机压比	6
高压压气机效率	0.85
燃烧室燃油流量/（kg/s）	3.15
加力燃烧室燃油流量/（kg/s）	6.69
燃烧效率	0.995
高压涡轮效率	0.9
高压涡轮导向器冷却气量/%	12.06
高压涡轮转子冷却气量/%	5.94
低压涡轮效率	0.91
低压涡轮导向器冷却气量/%	4.48
低压涡轮转子冷却气量/%	2.52
喷管速度系数	0.985
高压轴转速/（r/min）	15200
低压轴转速/（r/min）	10080
机械效率	0.995

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表 2 F135校验结果

Table 2. Verification results of F135

模式	参数	参考值	仿真值	误差/%
不开加力	推力/kN	124.6	128.36	3.02
	耗油率/（g/（kN·s））	25.28	24.54	−2.93
	高压涡轮进口温度/K	2175	2179.5	0.21
加力	推力/kN	193.35	202.23	4.59
	耗油率/（g/（kN·s））	50.89	48.66	−4.38
	喷管开度	1.625	1.587	−2.35
	加力燃烧室出口温度/K	2300	2313.89	0.6

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表 3 VCE变几何参数表

Table 3. Variable geometry parameters table of VCE

参数	含义
α_fan/（°）	风扇导叶角度
α_CDFS/（°）	CDFS导叶角度
α_FVABI	FVABI开度
α_RVABI	RVABI开度
k_open	MSV打开或关闭

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