Coupling design method for thermodynamic cycle and flow path geometric parameters of turbine engine
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摘要:
针对未来先进发动机匹配机制复杂，热力循环参数及部件性能与流路几何参数高度耦合，且概念设计阶段输入参数较为欠缺的特点，建立具有通用性的耦合仿真架构和流程；基于经验关系式及部件耦合图，形成热力循环参数与流路几何参数耦合设计方法，可在不同的热力循环参数下预测部件效率水平，并得到关键叶轮部件的进出口尺寸参数。利用上述方法，对混排涡扇发动机、自适应变循环发动机、“双变”循环发动机模型开展仿真验证。结果表明：本文方法得到的旋转部件流路几何参数估算值与实际设计值或文献设计值的误差可控制在10%以内，达到美国NASA发动机流路尺寸预测精度，可有效缩短方案迭代周期，减小后期颠覆设计风险，为发动机详细设计提供参考。
Abstract:Future advanced engines face challenges such as complex matching mechanisms, and a high degree of coupling between thermodynamic cycle parameters, component performance, and flow path geometry. Additionally, the conceptual design phase offer suffers from a lack of input parameters. To address these issues, a general-purpose coupled simulation architecture and process were established. Based on empirical correlations and component coupling diagrams, a coupled design method for thermodynamic cycle parameters and flow path geometric parameters was developed. This method enabled the prediction of component efficiency levels under different thermodynamic cycle parameters and yielded the inlet and outlet dimensions of key impeller components. Using the proposed method, simulation validations were carried out on three engine models: a mixed-flow turbofan engine, an adaptive variable-cycle engine, and a “dual variable” cycle engine. The results showed that the estimated flow path geometric parameters of rotating components obtained by this method had errors within 10% compared with actual design values or values reported in the literature, achieving a level of prediction accuracy for engine flow path dimensions comparable with that of NASA. This approach effectively shortens the iteration cycle in the scheme design phase, reduces the risk of major design changes in subsequent stages, and provides valuable reference for detailed engine design.
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Key words:
- turbine engine /
- overall performance /
- geometric parameters /
- cycle parameters /
- coupling design
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图 3 不同技术水平下压缩部件多变效率曲线
Figure 3. Polytropic efficiency characteristics of compression components at different technology levels
图 6 考虑间隙影响的涡轮效率修正
Figure 6. Turbine efficiency correction considering tip clearance effects
图 7 考虑低雷诺数影响的涡轮效率修正
Figure 7. Turbine efficiency correction considering low Reynolds number effects
图 8 涡轮效率及尺寸耦合计算流程
Figure 8. Turbine efficiency and dimension coupled calculation process
图 10 变效率和定效率的对比
Figure 10. Comparison between variable efficiency and fixed efficiency
图 14 小涵道比涡扇发动机叶尖半径误差对比
Figure 14. Comparison of blade tip radius errors for a low-bypass-ratio turbofan engine
图 17 “双变”循环发动机原理构型
Figure 17. Principle-based configuration of dual-variable cycle engine
图 18 “双变”循环发动机叶尖半径误差对比
Figure 18. Dual-variable cycle engine tip radius error comparison
表 1 中涵道比涡扇发动机总体循环参数
Table 1. Overall cycle parameters of a medium-bypass-ratio turbofan engine
空气流量/（kg/s） 总增压比 涵道比 涡轮前温度/K 101.1 25.0 0.7 1672 
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表 2 小涵道比涡扇发动机总体循环参数
Table 2. Overall cycle parameters of a low-bypass-ratio turbofan engine
空气流量/（kg/s） 总增压比 涵道比 涡轮前温度/K 110 25.0 0.3 1 860
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表 3 自适应循环发动机总体循环参数
Table 3. Overall cycle parameters of adaptive variable cycle engine
参数 数值 参数 数值 高度/km 11 马赫数 1.5 前风扇压比 1.8 核心风扇压比 1.37 高压压气机压比 4.65 第一涵道比 0.2 第二涵道比 0.25 第三涵道比 0.15 涡轮前温度/K 1 833
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表 4 “双变”循环发动机总体循环参数
Table 4. Overall cycle parameters of dual-variable cycle engine
参数 数值 参数 数值 高度/km 0 马赫数 0 流量/（kg/s） 125 后风扇压比 1.28 高压压气机压比 4.33 第一涵道比 1.44 第二涵道比 0.22 第三涵道比 0.06 主燃温度/K 1600 双变温度/K 1473
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