转子67叶片与端壁组合设计的优化与数值研究

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-05-18 DOI:10.1515/tjj-2023-0011

Xin Li, Tong Meng, Lingchen Zhou, Weiwei Li, L. Ji

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引用次数: 0

摘要

摘要在这项工作中，提出了一种使用扩展自由形式变形技术的叶片和端壁的组合设计，并在跨音速压缩机转子（NASA转子67）上实现。通过数值研究和克里格代理模型优化方法，探讨了最佳组合设计。因此，只需在15岁以下修改轮毂和叶片 % 跨度，峰值绝热效率增加0.4 % 并且在所有操作条件下的整体空气动力学性能也得到改善。分析表明，增大的轮毂与叶片的二面角抑制了边界层的相交和发展。同时，优化的轮毂改变了压力分布，防止了横流的迁移。结果，角部的低能流在下游加速，分离受到限制，从而有效地提高了角部区域的通流能力和空气动力学性能。

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Optimization and numerical investigation of combined design of blade and endwall on rotor 67

Abstract In this work, a combined design of blade and endwall using the Extended Free Form Deformation technique is proposed and implemented on a transonic compressor rotor (the NASA Rotor 67). The best combined design is explored by numerical investigations and optimization via Kriging surrogate model method. As a result, by only modifying the hub and blade under 15 % span, the peak adiabatic efficiency is increased by 0.4 % and the overall aerodynamic performance for all operating conditions is also improved. An analysis shows that the enlarged dihedral angle between the hub and blade restrains boundary layer intersection and development. Meanwhile, the optimized hub changes the pressure distribution and prevents migration of cross-flow. As a result, the low-energy flow in the corner is accelerated downstream and the separation is limited, leading to an effective improvement in throughflow capability and aerodynamic performance in the corner region.

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.