Wire-duct precipitator field and charge computation using finite element and characteristics methods

Davis, J. L.; Hoburg, James F.

doi:10.1016/0304-3886(83)90006-2

Cited by 121 publications

(39 citation statements)

References 4 publications

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“…[A 'current tube' is analogous to a streamtube in which charge (fluid) is flowing under the effect of an electric field (pressure gradient).] The boundaries of the current tube are determined by the electric field lines when only the drift current is considered, as has been derived previously, for example, by Davis & Hoburg [17]. An example of a current tube is shown in figure 1 for a two-dimensional wire-to-cylinder geometry.…”

Section: (B) Theoretical Limit On Thrust Densitymentioning

confidence: 95%

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Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Gilmore

Barrett

2015

Proc. R. Soc. A.

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ResearchCite this article: Gilmore CK, Barrett SRH. 2015 Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion. Proc. R. Soc Previous work has characterized electrohydrodynamic (EHD) thruster performance, determining that thrust-to-power ratios are comparable with that of conventional propulsion at the laboratory scale. Achievable thrust density of EHD propulsion has yet to be experimentally quantified and could be a limiting factor in its application. In this paper, we quantify the achievable thrust density for a wire-to-cylinder electrode geometry using positive corona discharges for electrode pairs operating in parallel and in series. Geometric parameters, including the non-dimensional inter-pair and stage spacings, are varied, and the effect on current and thrust is measured. We estimate a maximum thrust per unit area of 3.3 N m −2 and a maximum thrust per unit volume of 15 N m −3 , which we compare with the characteristic thrust density of a range of aircraft. We find that trade-offs exist between thrust density and the achieved thrust-to-power ratio, where increases in the former through either increased power input or pair packing density lead to decreases in the latter. We conclude that EHD propulsion has the potential to be viable from both an energy efficiency perspective (our previous study) and a thrust density perspective (this paper), with the greatest likelihood of viability for smaller aircraft such as unmanned aerial vehicles.

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Section: (B) Theoretical Limit On Thrust Densitymentioning

confidence: 95%

“…This has also motivated literature focused on developing computational models to solve the EHD governing equations [12][13][14][15][16][17]. In aerospace engineering, research efforts have focused on using dielectric barrier discharges (DBDs) to provide aerodynamic flow control to prevent subsonic boundary layer separation over aerofoils [18][19][20].…”

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confidence: 99%

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Gilmore

Barrett

2015

Proc. R. Soc. A.

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“…The model employed an iterative model based on the finite element method for computing electric potential structure in wire-duct electrostatic precipitators for an assumed charge density distribution by solving Poisson's equation, and the method of characteristics for computing charge density structure for an assumed electric field distribution [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

“…There are several attempts to compute the electric field and I-V characteristics of different ESP geometries including wire-cylinder [8,10,11]and wire-ductarrangements [1][2][3][4][6][7][8][9][10][11]. The analysis of the ionized-field in these arrangements is based onboundary element method (BEM) [3], charge simulation method (CSM) [4],finite volume characterization method (FVM) [8],finite element method combined with the method of characteristics (MOC) [1,2], FDM combined with MOC [7]and BEM combined with FDM [6].…”

Section: Introductionmentioning

confidence: 99%

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Corona Performance in Wire-cylinder ESP without Particle Loading

Abdel‐Salam

El-Mohandes

El-deen

2016

MATEC Web of Conferences

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This paper is aimed at investigating thoroughly the corona performance in the wirecylinder electrostatic precipitor (ESP) without suspended particles. The onset voltage of negative corona on the discharge wire is calculated based on the criterion of self-sustained discharge. The ionized field in the ESP is mathematically modeled for calculating the spatial distribution of the space-charge density due to the corona ions as well as the components of the electric field including the applied field and the field due to the space charge. This is in addition to the calculation of the current-voltage characteristics of the ESP.

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Highly stable finite volume based relaxation iterative algorithm for solution of dc line ionized fields in the presence of wind

Li¹,

Ciric²,

Raghuveer³

1997

Int. J. Numer. Model.

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Wire-duct precipitator field and charge computation using finite element and characteristics methods

Cited by 121 publications

References 4 publications

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Corona Performance in Wire-cylinder ESP without Particle Loading

Highly stable finite volume based relaxation iterative algorithm for solution of dc line ionized fields in the presence of wind

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