一种新型泡腾雾化器的设计研究

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE
I. Levitsky, Nikolay Razoronov
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引用次数: 0

摘要

摘要我们提出了一种新型的泡腾雾化器,其衬套安装在垂直于通道轴线的液体通道中。衬套有孔,通过这些孔注入空气以产生气泡。空气被释放到通道和衬套之间的间隙中。本研究评估了气泡的雾化质量。在没有出口喷嘴和喷嘴直径为2mm的情况下,在不同配置下,以多种水和空气流速进行雾化器测试。雾化器的设计使小气泡的均匀气泡流动成为可能。当ALR=0.012–0.036,水流量分别为1.67和2.17 L/min(无出口喷嘴)时,0.2–0.4 mm的气泡直径占气泡总数的40–50%。直径为0.8–1.0 mm的气泡数量不超过5%。在将注入参数ε增加两次后,气泡的平均直径保持不变。经过测试,带有一个衬套、直径为2 mm的出口喷嘴和1.67 L/min的水流量的雾化器在0.02–0.12的ALR值下产生的粒径为SMD=32–100μm。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Study of a new effervescent atomizer design
Abstract We propose a new type of effervescent atomizer with bushings installed in the liquid channel perpendicular to the channel’s axis. Bushings have holes through which air is injected to create bubbles. The air is released into the gap between the channel and the bushing. This investigation evaluates the bubbles’ atomization quality. Atomizer tests were conducted at multiple water and air flow rates, under different configurations, without an exit nozzle and with a 2 mm nozzle diameter. The atomizer’s design enables a homogenous bubble flow with small air bubbles. At an ALR = 0.012–0.036 and water flow rates of 1.67 and 2.17 L/min without an exit nozzle, bubble diameters of 0.2–0.4 mm comprised 40–50% of the total number of bubbles. The number of the bubbles with diameters of 0.8–1.0 mm does not exceed 5%. After increasing the injection parameter ε twice, the average diameter of the bubbles remained constant. Upon testing, an atomizer with one bushing, 2 mm-diameter outlet nozzle, and a water flow rate of 1.67 L/min produced particle diameters of SMD = 32–100 μm at ALR values of 0.02–0.12.
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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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