空气喷射增强S型管道的性能和流分离控制

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE International Journal of Turbo & Jet-Engines Pub Date : 2022-05-12 DOI:10.1515/tjj-2021-0063
Xi Gao, Zhiyuan Cao, Xiang Zhang, Fei Zhang, Jing Yang, Bo Liu
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引用次数: 0

摘要

摘要为了研究喷射对S型管流分离的影响机理,研究了不同的单孔方案,并与双孔方案进行了比较。结果表明,注射成型可以改善S型管的性能。本研究中的最佳方案是两个孔位于同一轴向位置的双孔注射方案。通过在每个孔中注入0.46%的注入系数,实现了流分离减少和损失系数减少16.9%。其流动机理是:首先,通过空气喷射将高动量流体喷射到分离流中;二次高动量流通过注入涡流被输送到下壁附近。还讨论了位置效应、注入流量效应和孔形效应。对于双孔方案,两个孔位于不同轴向位置的方案通过混合两个注入涡流产生更强的涡流,并增强二次流。虽然减少了流动分离,但在出口处形成了严重的不均匀流场。由于双y方案在S型风管出口处实现的旋流较少,因此可以为下游压缩机提供更均匀的流场,并具有更好的控制效果。
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Performance enhancement and flow separation control in an S-duct by air injection
Abstract With the purpose of investigating the effect mechanism of injection on flow separation of the S-duct, different single-hole schemes were investigated and compared with double-hole schemes. Results show that, the performance of S-duct can be improved by using injection. The optimal scheme in this study is a double-hole injection scheme with two holes located at the same axial position. Flow separation reduction and a 16.9% reduction of loss coefficient were achieved by injection with an injection coefficient of 0.46% in each hole. The flow mechanisms are that, firstly, high momentum fluid is injected to separated flow by air injection; secondary, high momentum flow is transported to flow near downside wall by injection vortex. The position effect, injection flow rate effect and hole shape effect were also discussed. For double-hole scheme, the scheme with two holes located different axial positions generates a stronger vortex by mixing two injection vortexes and enhances secondary flow. Though the flow separation is reduced, a severe nonuniform flow field at outlet is formed. Due to the less swirling flow achieved at outlet of S-duct by Double-y scheme, it can offer a more uniform flow field for downstream compressor and has a better control effectiveness.
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来源期刊
International Journal of Turbo & Jet-Engines
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
36
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.
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