Computation and plotting of solid particle flow in rotating cascades

Hussein, M. F.; Tabakoff, W.

doi:10.1016/0045-7930(74)90002-4

Cited by 49 publications

(24 citation statements)

References 3 publications

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“…(1)(2)(3)(4) in the inlet flowfield. During the computations, the flow velocity and density are usually required at points within the orthogonal mesh.…”

Section: Trajectory Calculationsmentioning

confidence: 99%

Particle Dynamics of Inlet Flowfields with Swirling Vanes

Hamed

1982

Journal of Aircraft

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The particle trajectories are investigated for the inlet flowfield of a helicopter engine with swirling vanes and particle separator. The flowfield resulting from the swirling vanes is first computed on a hub-shroud midchannel stream surface. The trajectories of the solid particles are then determined in this flowfield, including particle impacts with the hub, tip, and vane surfaces. The particle rebounding velocity and direction after each impact is determined using empirical correlations derived from experiments conducted in a special tunnel. Different particle sizes are considered, and the resulting trajectories and separator effectiveness are presented. and Nomenclature B = tangential space between blades C p -specific heat at constant pressure F = vector normal to midchannel stream surface proportional to tangential pressure gradient H = stagnation enthalpy TV = unit vector normal to the vane, hub, or tip p = stagnation pressure R = gas constant r = radial distance from the axis r c = radius of curvature of meridional streamline 5 = entropy s = distance along orthogonal mesh lines in through-flow direction T = temperature t = distance along orthogonal mesh lines in direction across flow T = unit vector tangent to the vane, hub, or tip u = normalized stream function V = flow velocity V p -particle velocity z = axial coordinate ot = angle between meridional streamline and axial direction /3 = angle between flow velocity vector and meridional plane j8 7 = angle between impacting particle velocity and the surface 6 = angular coordinate p = gas density p p = particle density r =time = angle between s line and axial direction Subscripts i = inlet conditions m = component in direction of meridional streamline TV = component normal to vane, hub, or tip surface n -f»a rti r«1p» r s t T Z = particle = component in radial direction = component in s direction = component in t direction = component tangent to vane, hub, or tip surface = component in axial direction = component in tangential direction Presented as Paper 81-0001 at

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“…(1)(2)(3)(4) in the inlet flowfield. During the computations, the flow velocity and density are usually required at points within the orthogonal mesh.…”

Section: Trajectory Calculationsmentioning

confidence: 99%

Particle Dynamics of Inlet Flowfields with Swirling Vanes

Hamed

1982

Journal of Aircraft

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“…Hussein and Tabakoff [11] pioneered particle trajectory simulations through rotating and stationary axial turbomachinery and the use of experimentally determined particle rebound factors. Elfeki and Tabakoff [12] demonstrated that in centrifugal compressors, panicle trajectories are consistently different as a consequence of the complex flow and its interaction with centrifugal force.…”

Section: Introductionmentioning

confidence: 99%

Predicting Blade Leading Edge Erosion in an Axial Induced Draft Fan

Corsini

Marchegiani

Rispoli

et al. 2012

Journal of Engineering for Gas Turbines and Power

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Induced draft fans extract coal flred boiler combustion products, including particles of un-burnt coal and ash. As a consequence of the particles, the axial fan blades' leading edges are subject to erosion. Erosion results in the loss of the blade leading edge aerodynamic proflle and a reduction of blade chord and effective camber that together degrade aerodynamic performance. An experimental study demonstrated that while the degradation of aerodynamic performance begins gradually, it collapses as blade erosion reaches a critical limit. This paper presents a numerical study on the evolution of blade leading edge erosion patterns in an axial induced draft fan. The authors calculated particle trajectories using an in-house computational fluid dynamic (CED) solver coupled with a trajectory predicting solver based on an original finite element interpolation scheme. The numerical study clarifles the influence of flow structure, initial blade geometry, particle size, and concentration on erosion pattern.

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“…1). Rotating blades are most susceptible to impact damage because their high rotational speeds result in large particle/TBC impact velocities, despite the relatively low velocities associated with the particles themselves [2]. Prior experiments and modeling [3e6] have shown that elastic waves are initiated in the TBC upon impact of a particle.…”

Section: Introductionmentioning

confidence: 99%

“…The conditions leading to FOD in a jet engine are complex and encompass a range of impact angles, impact speeds, particle sizes, particle compositions, and material temperatures [2]. Therefore, a dynamic finite element model has been developed to help the understanding and prediction of foreign object damage [4,5].…”

Section: Introductionmentioning

confidence: 99%