A method and device for designing a wide operating condition low-loss turbine blade

By determining the target design parameters and optimization functions of the turbine, constructing the basic airfoil geometric model, performing aerodynamic analysis and loss diagnosis, and executing three-dimensional stacking and radial load matching design, the problem of flow separation of turbine blades under a wide range of operating conditions was solved, turbine efficiency was improved and flight fuel consumption was reduced.

CN122413617APending Publication Date: 2026-07-17AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
AECC HUNAN AVIATION POWERPLANT RES INST
Filing Date
2026-06-05
Publication Date
2026-07-17

AI Technical Summary

Technical Problem

Turbine blades, under wide operating conditions, experience large variations in angle of attack, leading to flow separation, significant blade losses, and low turbine efficiency, which in turn increases fuel consumption during flight.

Method used

By determining the target design parameters and optimization functions of the turbine, a basic blade geometry model is constructed, aerodynamic analysis and loss diagnosis are performed, three-dimensional stacking and radial load matching design are executed, and the blade profile is optimized to reduce losses.

Benefits of technology

Under a wide range of operating conditions, reduce blade losses, improve turbine efficiency, and reduce fuel consumption for all flight missions.

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Abstract

本发明涉及涡轮发动机设计技术领域，公开了一种宽工况涡轮叶片设计方法及装置，本发明确定涡轮机的目标设计参数和目标优化函数；根据目标设计参数，构造涡轮机的基元叶型几何模型；根据涡轮机的基元叶型几何模型，对涡轮机进行气动分析与损失诊断；根据涡轮机的气动分析与损失诊断的结果，对涡轮机的基元叶型几何模型执行三维积叠与径向负荷匹配设计动作；根据目标优化函数，对涡轮机的基元叶型几何模型进行优化与验证。因此，本发明可以确保涡轮机的叶片在宽工况工作时，即使各排叶片的攻角变化大，也能防止叶片损失较大，还能提升涡轮效率。另外，本发明不但能提升涡轮机性能，而且还能降低飞行的全任务耗油量降低。
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