Xi Gao, Zhiyuan Cao, Xiang Zhang, Fei Zhang, Jing Yang, Bo Liu
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引用次数: 0
Abstract
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.
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.