Analysis Method for Inertial Particle Separator

Saeed, Farooq; Al-Garni, Ahmad

doi:10.2514/1.20245

Cited by 30 publications

(20 citation statements)

References 24 publications

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“…Fig. 2 Illustrations of a) typical axisymmetric helicopter engine particle separator (adapted from [4]) and b) proposed five-element airfoil configuration model for an IPS system [3].…”

Section: A Profoil Codementioning

confidence: 99%

“…A flow and trajectory analysis code [3] for the multi-element configuration-based IPS system analysis was used in the current program for sand-particle trajectory and impingement analysis. The IPS system analyzer is able to perform impingement analysis using spherical/nonspherical solid particles as well as water droplets for a range of Reynolds numbers (10 4 Re 5 10 5 ).…”

Section: A Flow and Trajectory Analysismentioning

confidence: 99%

“…It was proposed in [3] that a multi-element airfoil configuration IPS (Fig. 2b) be used instead of the current design (Fig.…”

mentioning

confidence: 99%

“…The operation life of a helicopter engine operating in sandy environments can be as short as 50 h [1,2]. Engine damage ranges from simple erosion in the engine blades to a completely inoperative engine with as little as one-half pound of sand [3]. In addition, the degrading of the performance and efficiency of the aircraft engine leads to increased fuel consumption and operational cost [1].…”

mentioning

confidence: 99%

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Design and Optimization Method for Inertial Particle Separator Systems

Al-Faris

Saeed

2009

Journal of Aircraft

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The paper presents a method for the design and optimization of a multi-element airfoil-based inertial particle separator. To facilitate design in an interactive manner, a MATLAB graphical user interface was developed with the following capabilities: 1) design of individual airfoil elements; 2) orientation and arrangement of the airfoils to form a multi-element airfoil-based inertial particle separator system by employing translational, scaling, and rotational functions; 3) analysis of the inertial particle separator system; and 4) optimum design of the inertial particle separator system using an evolutionary algorithm-based direct-search optimization technique. The design of individual airfoils was achieved through the use of the PROFOIL code, a state-of-the-art multipoint inverse airfoil design program. Multiple airfoils were arranged to form a multi-element airfoil-based inertial particle separator system subject to geometric constraints. A two-dimensional analysis tool for the multi-element airfoil was linked to the synthesis component of the graphical user interface to carry out flow and particle trajectory analysis component of the program. For the optimization component of the program, a computational objective function was implemented and coupled with a pattern search optimizer of the Direct Search Toolbox in MATLAB. Design and optimization was achieved using multivariable optimization. The paper presents two design examples to demonstrate the design method. Nomenclature C d = particle drag coefficient c = airfoil chord length D eq = equivolumetric or mean volumetric diameter F a = aerodynamic force F g = gravitational force g = gravitational acceleration constant i, k = unit direction vectors in the wind reference frame i p , k p = unit direction vectors in the body reference frame m p = particle mass, p V p n = surface normal vector p = ambient pressure Re = Reynolds number based on particle diameter, a D eq U= a r p = particle position S = particle surface projection on the U perpendicular plane S p = particle surface area t = time U = magnitude of particle relative velocity in the body reference frame, jUj U = particle relative velocity in the body reference frame, V a V p V a = freestream velocity in the body reference frame, u a i w a k V p = particle volume V p = particle velocity in the body reference frame, dr p =dt x, z = axes in the wind reference frame x p , z p = axes in the body reference frame z = pressure head = angle between the z p axis and z axis a = ambient air viscosity a = ambient air density p = particle mass density = shear stress

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“…Fig. 2 Illustrations of a) typical axisymmetric helicopter engine particle separator (adapted from [4]) and b) proposed five-element airfoil configuration model for an IPS system [3].…”

Section: A Profoil Codementioning

confidence: 99%

Section: A Flow and Trajectory Analysismentioning

confidence: 99%

“…It was proposed in [3] that a multi-element airfoil configuration IPS (Fig. 2b) be used instead of the current design (Fig.…”

mentioning

confidence: 99%

mentioning

confidence: 99%

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Design and Optimization Method for Inertial Particle Separator Systems

Al-Faris

Saeed

2009

Journal of Aircraft

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“…Several studies [11][12][13][14] have been conducted for establishing a computational fluid dynamics (CFD) method which will lead to an optimized and proper shape of an IPS under constraints representing diverse flight conditions. Commonly those constraints have a sufficient high efficiency value and geometrical dimensions.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of internal flow field and flow passage improvement of an inlet particle separator

Paoli

Wang

2011

Front. Energy

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By performing gas flow field numerical simulations for several inlet Reynolds numbers Re (from 2 Â 10 5 to 9 Â 10 5 ) and byflow ratios x (from 10% to 20%), the present study has proposed to improve the flow passage of an inlet particle separator. An adjacent objective of the study is to lower pressure losses of the inlet particle separator (IPS). No particle has been included in the gas flow for a k-epsilon turbulence model. The velocity distribution in different sections and the pressure coefficient C p along the duct have been analyzed, which indicates that there exist important low-velocity regions and vortices in the separation area. Therefore, the profile of streamlines along the original passage has been considered. This profile illustrated a vacuum region in the same area. All investigations suggest that the separation area is the most critical one for fulfilling the objective on pressure losses limitation. Then the flow passage improvement method has focused on the separation area. An improved shape has been designed in order to suit smoothly to the streamlines in this region. Similar numerical studies as those for the original shape have been conducted on this improved shape, confirming some considerable enhancements compared with the original shape. The significant vortices which appear in the original shape reduce in amount and size. Besides, pressure losses are greatly decreased in both outlets (up to 30% for high Reynolds number) and the flow is uniform at the main outlet. Subsequent engineering surveys could rely on expressions obtained for C p in both outlets which extend the pressure losses for a wide range of inlet Reynolds numbers. As a result, the numerical calculations demonstrate that the flow passage improvement method applied in this study has succeeded in designing a shape which enhances the flow behavior.

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