Journal Articles

Permanent URI for this collectionhttps://idr.nitk.ac.in/handle/123456789/19884

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Author: search.filters.author.Yepuri, Y.G.Subject: search.filters.subject.Experimental investigations

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    Experimental study of adiabatic cooling effectiveness on an effusion cooled test plate with machined ring geometries
    (Begell House Inc. orders@begellhouse.com, 2018) Jesuraj, J.; Rajendran, R.; Kumar, G.N.; Yepuri, Y.G.
    The present study deals with experimental investigation of adiabatic cooling effectiveness on an effusion cooled test plate with machined ring geometries. Initial tests were performed on an effusion cooling holes. The cooling effectiveness at the beginning of effusion holes is lower, and it increases in the flow direction mainly due to the additive effect of film cooling effectiveness of the effusion cooling geometry. Subsequent tests were done with machined ring geometries fixed ahead of effusion cooling hole geometry to improve the cooling effectiveness before the beginning of effusion cooling holes. These machined ring geometries act as a wall jet and reduce the hot side heat load by film cooling performance. Tests were performed at a coolant to mainstream density ratio of 1.3 and at blowing ratios ranging from 0.5 to 2.5. Increase in the blowing ratio shows an increase in the cooling effectiveness. Comparison results show that the adiabatic cooling effectiveness increases significantly before the effusion cooling holes in the presence of machined ring geometries at all blowing ratios. © 2018 by Begell House, Inc.
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    Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
    (Walter de Gruyter GmbH, 2023) Vinay, C.A.; Gottekere Narayanappa, K.; Yepuri, Y.G.
    Turboprop engines require an exhaust nozzle or stub to duct the engine exhaust flue gas outboard of the aircraft. The design of these exhaust stubs are dictated primarily by the aircraft's configuration. In pusher aircraft, the exhaust stubs are designed to minimize the exposure of the flue gases from the engine exhaust on the propeller blades and fuselage. A fluid-thermal-structure coupling analysis is performed to understand the thermal effects of the engine exhaust jet flow on the thermo-mechanical behavior of pusher configured light transport aircraft propeller and structure. The steady thermal flow field of the aircraft with forward and reverse thrust, in which propeller blade angle variations were analyzed for different aircraft speed. The present work investigates a three-dimensional analysis of flow around the nacelle-airframe and the effect of exhaust flue gas impingement on the propeller blade surface. Based on the insights from the numerical results, the designed exhaust duct was integrated on the aircraft and carried out ground static and flight testing for various flight operating conditions in which propeller blade and fuselage surface temperature were measured. Numerical and experimental results are compared and validated for certain flight conditions and found satisfactory. © 2023 De Gruyter. All rights reserved.