穿孔壁对控制马赫数为 5 至 9 的 SWBLI 造成的分离的影响

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2024-06-11 DOI:10.1515/tjj-2024-0014

Dinesh Babu R, Ganapati N. Joshi, Sunil Chandel, Ranjan Kumar Mishra

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引用次数: 0

摘要

摘要对混合压缩喷气发动机进气道进行了数值模拟，以研究冲击波引起的边界层分离导致分离气泡（SB）形成的特征。分析采用了二维-RANS方法和不同马赫数下的SST k-ω湍流模型。为了提高性能，进气口被设计成三斜坡进气口。随着马赫数的变化，斜冲击波与边界层相互作用形成的分离气泡的大小也会发生变化，从而影响进气效率和发动机的整体效率。除了传统的控制技术外，最常用的放气技术是结合式放气。在进气口的不同位置设计和分析了局部和分布式放气技术。这些技术可减小进气道内分离气泡的大小。在发动机进气道上打孔还能提高进气效率和发动机的整体性能。

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Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9

Abstract The mixed compression scramjet engine intake was numerically simulated to study the characteristic of shock wave induced boundary layer separation leading to the formation of the separation bubble (SB). The analysis employed a 2D-RANS method with SST k-ω turbulence model at different Mach numbers. The intake is designed as a three-ramp intake for improved performance. As the Mach number varies, the size of the separation bubble formed due to the interaction of oblique shock waves with the boundary layer also varies, affecting both intake the efficiency and overall efficiency of the engine. Apart from traditional control techniques, the most preferred bleed technique is incorporated. Localised & distributed bleed techniques are designed and analysed within the intake at different locations. These techniques result in a reduction in the size of the separation bubble within the intake. Establishing perforation in the engine intake also increases the intake efficiency and overall engine performance.

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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.