Aircraft engines operating in areas where the atmosphere is polluted by small solid particles are typical examples of jet engines operating under hostile atmospheric environment. The particles may be different kinds of sand, volcanic ashes or others. Under these conditions, the gas and particles experience different degrees of turning as they flow through the engine. This is mainly due to the difference in their inertia. This paper presents the results of an investigation of the solid particle dynamics through a helicopter engine with inlet particle separator. The particle trajectories are computed in the inlet separator which is characterized by considerable hub and tip contouring and radial variation in the swirling vane shape. The nonseparated particle trajectories are determined through the deswirling vanes and the five stage axial flow compressor. The results from this study include the frequency of particle impacts and the erosion distribution on the blade surfaces.
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September 1987
Research Papers
Compressor Erosion and Performance Deterioration
W. Tabakoff
W. Tabakoff
Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati, Cincinnati, Ohio 45221
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W. Tabakoff
Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati, Cincinnati, Ohio 45221
J. Fluids Eng. Sep 1987, 109(3): 297-306 (10 pages)
Published Online: September 1, 1987
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Received:
July 29, 1986
Online:
October 26, 2009
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Discussion: “Compressor Erosion and Performance Deterioration” (Tabakoff, W., 1987, ASME J. Fluids Eng., 109, p. 297)
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Tabakoff, W. (September 1, 1987). "Compressor Erosion and Performance Deterioration." ASME. J. Fluids Eng. September 1987; 109(3): 297–306. https://doi.org/10.1115/1.3242664
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