涡轴-涡扇变循环发动机模态转换控制规律设计方法

杨岢钰; 贾琳渊; 陈玉春; 任成; 张鑫

doi:10.13224/j.cnki.jasp.20240697

涡轴-涡扇变循环发动机模态转换控制规律设计方法

doi: 10.13224/j.cnki.jasp.20240697

杨岢钰^1,,
贾琳渊^1,*, ,,
陈玉春¹,
任成¹,
张鑫²

1.
西北工业大学动力与能源学院，西安 710072
2.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 国家自然科学基金面上项目（52372397）

详细信息

作者简介:
杨岢钰（2001-），男，博士生，主要从事航空发动机总体设计。E-mail：yangkeyu@mail.nwpu.edu.cn

通讯作者:
贾琳渊（1989-），男，副教授，博士，研究领域为航空发动机总体设计。E-mail：jialinyuan@nwpu.edu.cn

中图分类号: V438
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出版历程
- 收稿日期: 2024-10-14
- 网络出版日期: 2025-07-14

Design method for mode transition control schedule of turboshaft-turbofan variable cycle engines

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
针对涡轴-涡扇变循环发动机模态转换过程性能优化的需求，提出了一种以输出功率为目标同时可考虑变几何部件调节速率限制的模态转换控制规律设计方法。基于发动机的物理特性和部件级性能模型，采用逆算法和过渡态性能隐式计算格式开发了涡轴-涡扇变循环发动机过渡态直接求解方法。基于该方法，提出了一种可以实现直接功率控制和给定压缩部件工作点的模态转换控制规律设计方法。计算结果表明：在飞行高度H=1 km、飞行马赫数Ma=0.3条件下，涡轴模态转涡扇模态的时间约为4.0 s，涡扇模态转涡轴模态的时间约为2.1 s，功率连续平稳变化。该方法可为解决涡轴-涡扇变循环发动机模态转换这一技术难题提供重要的参考。
- 涡轴-涡扇变循环发动机 /
- 模态转换 /
- 控制规律设计方法 /
- 直接求解方法 /
- 直接功率控制
Abstract:
The need for performance optimization during the mode transition process of a turboshaft-turbofan variable cycle engine was addressed. A mode transition control schedule design method focused on output power was proposed while considering the adjustment rate limits of variable geometry components. Based on the engine’s physical characteristics and component-level performance model, a direct solution method for the transition state of the turboshaft-turbofan variable cycle engine was developed using inverse algorithms and implicit calculation formats for transition state performance. Using this method, a control schedule design method was proposed, enabling to realize direct power control and set the operating point of compression components during mode transition. The results showed that under conditions of flight height H=1 km and Mach number Ma=0.3, the transition time from turboshaft mode to turbofan mode was approximately 4.0 s, and that from turbofan mode to turboshaft mode was approximately 2.1 s, with smooth and continuous power changes. This method could provide important reference for solving the technical challenge of mode transition in turboshaft-turbofan variable cycle engines.
- turboshaft-turbofan variable cycle engines /
- mode transition /
- design method for mode transition control schedule /
- direct solution method /
- direct power control

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图 1 轴扇发动机结构示意图

Figure 1. Schematic diagram of turboshaft-turbofan engine structure

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图 2 轴扇发动机截面示意图

Figure 2. Schematic diagram of turboshaft-turbofan engine cross-section

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图 3 定几何隐式格式直接求解法流程图

Figure 3. Flow chart of direct solution method in fixed geometry implicit format

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图 4 涡扇模态验证结果

Figure 4. Validation result of turbofan mode

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图 5 涡轴模态验证结果

Figure 5. Validation result of turboshaft mode

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图 6 转模态控制规律设计方法流程图

Figure 6. Flow chart of mode-transition control schedule design method

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图 7 涡轴模态转涡扇模态仿真结果

Figure 7. Simulation result of turboshaft mode to turbofan mode

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图 8 涡扇模态转涡轴模态仿真结果

Figure 8. Simulation result of turbofan mode to turboshaft mode

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图 9 功率导数变化曲线

Figure 9. Variation curves of the power derivative

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表 1 不同模态对应的发动机传统模型

Table 1. Traditional engine models corresponding to different modes

发动机模态	控制变量	自变量	残差方程
涡轴	W_fb, n₁	β_f, β_fl, β_c, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h
涡扇	W_fb	β_f, β_fl, β_c, n₁, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h, δP_l
转模态	W_fb, n₁	β_f, β_fl, β_c, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h

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表 2 隐式计算格式动态模型

Table 2. Dynamic model of implicit algorithm

编号	给定参数	自变量	残差方程
1	n₁, T₄	β_f, β_fl, β_c, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h
2	n₁, ζ₄	β_f, β_fl, β_c, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h
3	n₁, β_c	β_f, β_fl, T₄, n₂, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h
4	n₁, n₂	β_f, β_fl, β_c, T₄, π_ht, π_lt	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h

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表 3 直接求解法模型

Table 3. Model of direct solution method

编号	给定参数	自变量	残差
1	n₁, T₄, P_op, β_fl	β_f, β_c, n₂, π_ht, π_lt, A₈, A_8d	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h, δP_out
2	n₁, β_C, P_op, β_fl	β_f, T₄, n₂, π_ht, π_lt, A₈, A_8d	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h, δP_out
3	n₁, n₂, P_op, β_fl	β_f, β_c, T₄, π_ht, π_lt, A₈, A_8d	δW_c, δW_g,4, δW_g,5, δW_g,9, δW_g,9d, δP_h, δP_out

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表 4 模态转换过程约束条件

Table 4. Constraints for modal translate

参数	限制范围	限制值
压气机喘振裕度/%	最小值	15
涡轮前温度/K	最大值	1730
燃烧室油气比	最大值	0.029^[26]
燃烧室油气比	最小值	0.006
喷管收缩速率/（%/s）	最大值	12.0
喷管扩张速率/（%/s）	最大值	16.7

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