Numerical study on the effect of distortion of S-duct on flow field and performance of a full annulus transonic fan

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-05-26 DOI:10.1515/tjj-2023-0019

Zhiyuan Cao, Xin Li, Cheng Song, Ping Huang, Jing Yang, Bo Liu

引用次数: 0

Abstract

Abstract To reveal the influence of distortion of S-duct on the flow field and performance of transonic fan, full annulus unsteady numerical simulation was carried out under S-duct/fan integrated condition. This study focuses on the coupling flow of S-duct/fan integrated condition under peak efficiency (PE) condition and near stall (NS) condition. Results show that, compared with the condition that S-duct or fan is investigated alone, the distortion of S-duct is suppressed under S-duct/fan integrated condition. The curved structure of S-duct is the important reason for the flow migration from undistorted region to distortion region. Higher inlet relative Mach number and more work input of the rotor are observed in the counter-swirl region. The flow separation in S-duct is weakened under NS condition compared with that of PE condition. Counter-swirl region of blade tip has larger region of blockage, and rotating stall inception is most likely to occur in this region.

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s型导管畸变对全环空跨音速通风机流场及性能影响的数值研究

摘要为了揭示s型风管畸变对跨声速通风机流场及性能的影响，在s型风管/通风机一体化条件下进行了全环空非定常数值模拟。研究了s -风管/风机一体化工况在峰值效率工况和近失速工况下的耦合流动。结果表明，与单独研究s -风管或风机相比，s -风管/风机一体化条件下s -风管的畸变得到了抑制。s型管道的弯曲结构是流动从未变形区向变形区迁移的重要原因。在反旋区，进气道相对马赫数增大，转子的功输入增大。与PE条件相比，NS条件下s管内流动分离减弱。叶尖逆旋区堵塞面积较大，该区域最容易发生旋转失速。

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.