Design optimization of a supersonic through-flow fan rotor based on the blade profiles

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-07-24 DOI:10.1515/tjj-2022-0082

Jutao Yang, L. Ji, Yuxin Shen, Lingchen Zhou

引用次数: 0

Abstract

Abstract In this study, the authors propose an optimization process to design the baseline rotor of a supersonic through-flow fan (STFF) at an inlet Mach number of 2.0 based on Genetic Algorithm. Unlike the improvement in performance brought about by the pre-compression of conventional supersonic profiles in the presence of axial pressure flow, pre-compression did not help improve the performance of the rotor of the STFF. The efficiency of elements of the blade at spanwise heights of 10 %, 50 %, and 90 % increased by 2.47 %, 1.95 %, and 2.49 %, respectively. The performance of the rotor of the STFF that was reconstructed by stacking the optimized elements of the blade was improved at the design point as well as in off-design conditions by using three-dimensional computational fluid dynamics (CFD) simulations. The performance of the blade also improved considerably, with increases of by 2.46 % and 9.59 % in its isentropic efficiency and the overall pressure ratio, respectively.

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基于叶型的超声速贯流风扇转子优化设计

摘要在本研究中，作者提出了一种基于遗传算法的超音速贯流风扇（STFF）基线转子优化设计方法，该方法的入口马赫数为2.0。与在存在轴向压力流的情况下对传统超声速剖面进行预压缩所带来的性能改进不同，预压缩无助于提高STFF转子的性能。叶片元件在翼展方向高度为10时的效率 %, 50 %, 和90 % 增加2.47 %, 1.95 %, 和2.49 %, 分别地通过使用三维计算流体动力学（CFD）模拟，在设计点和非设计条件下，通过堆叠叶片的优化元件重建的STFF转子的性能得到了改善。叶片的性能也得到了显著改善，增加了2.46 % 和9.59 % 其等熵效率和总压力比。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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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.