Study of a new effervescent atomizer design

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE
I. Levitsky, Nikolay Razoronov
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Abstract

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.
一种新型泡腾雾化器的设计研究
摘要:提出了一种新型的泡腾式雾化器,其衬套安装在垂直于通道轴线的液体通道内。衬套上有孔,空气通过这些孔被注入形成气泡。空气被释放到通道和衬套之间的空隙中。对气泡的雾化质量进行了评价。雾化器试验在多种水和空气流速下进行,在不同的配置下,没有出口喷嘴,喷嘴直径为2mm。雾化器的设计使均匀的气泡流与小气泡。在ALR = 0.012-0.036,水流速分别为1.67和2.17 L/min时,气泡直径为0.2-0.4 mm,占气泡总数的40-50%。直径0.8 ~ 1.0 mm的气泡数量不超过5%。将注入参数ε增大2倍后,气泡的平均直径保持不变。经测试,一个衬套、直径2mm的出口喷嘴、水流量为1.67 L/min的雾化器,在ALR为0.02 ~ 0.12的条件下,产生的SMD粒径为32 ~ 100 μm。
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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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