Browsing by Author "Vinay, C.A."

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    Aero-Thermal Investigation on Commuter Category Turboprop Aircraft Engine Nacelle
    (Springer Science and Business Media Deutschland GmbH, 2024) Vinay, C.A.; Kumar, G.N.; Iyengar, S.V.; Pugazhendhi, T.
    In aircraft industry, the development of composite materials for increased strength and reduced weight is always a priority. The external body of aircraft, i.e. fuselage, nacelle, wings etc., is made of Al alloy and composites. A nacelle of a light turbo-prop tractor-configured aircraft, houses hot components like engine and subsystem. The nacelle is also made of thermally sensitive composite material; hence, it requires specified thermal management study. Thermal ventilation is done by inlet scoops and louvre outlet which keeps the engine and nacelle bay region in lower temperature safe for nacelle surface. Aero-thermal analysis is performed on the engine and nacelle bay ventilation, and the temperature results of the computation fluid dynamics (CFD) analysis is used in assessing the suitable material and its mechanical properties degradation with respect to temperature. For numerical study, a simplified nacelle, engine, and subsystem geometry are considered. ANSYS ICEM CFD™ and CATIA commercial software is used for geometry preparation and tetra meshing. ANSYS Fluent is used as a solver with SST k − ω viscous model to capture thermal values at the geometry surfaces. © 2024, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
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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.