Study of a new effervescent atomizer design
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Inna Levitsky
and
Nikolay Razoronov
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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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This study was supported by an internal funding program of SCE – Shamoon College of Engineering to Dr. Inna Levitsky.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Articles in the same Issue
- Frontmatter
- Characterization of titanium grade 5 alloy compressor blade in a jet engine using advanced materials for optimum thrust production
- Numerical investigation of total temperature distortion problem in a multistage fan based on body force approach
- Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine
- Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario
- Active fault tolerant control of turbofan engines with actuator faults under disturbances
- Modeling and mode transition simulation of over-under turbine based combined cycle (TBCC) propulsion system based on inlet/engine matching
- Numerical analysis of high temperature gas flow through conical micronozzle
- Simulation and analysis of an aero-engine combustor with a slinger fuel injection system
- Influence of plasma-chemical products on process stability in a low-emission gas turbine combustion chamber
- Influence of nozzle exit geometrical parameters on supersonic jet decay
- Experimental investigation on mixing characteristics of high speed co-flow jets by using tabbed chevron nozzle
- Study of a new effervescent atomizer design
