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CFD Model of the Turboprop Engine Hot Part: Bay Cooling

[+] Author Affiliations
Goran Simeunovic, Lukáš Popelka, Petr Hatschbach

Czech Technical University in Prague, Prague, Czech Republic

Paper No. IMECE2018-87066, pp. V08AT10A005; 6 pages
  • ASME 2018 International Mechanical Engineering Congress and Exposition
  • Volume 8A: Heat Transfer and Thermal Engineering
  • Pittsburgh, Pennsylvania, USA, November 9–15, 2018
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-5211-8
  • Copyright © 2018 by ASME


The bay cooling of a specific new turboprop engine is investigated in this paper. The new ATP turboprop engine has additional jets with hot air stream close to the PT. This considerably increases the temperature inside the first nacelle compartment in the hot engine part around the engine combustion chamber. In order to achieve the optimal temperature conditions for engine parts inside the nacelle in the critical operating regime (triple red line), a new bay cooling system is proposed. Using the existing standard (National Advisory Committee for Aeronautics) NACA inlet at the front of the nacelle, two additional groups of ribs on rear part of front nacelle compartment and standard nacelle gaps (around exhausts), the temperature in the front part of the nacelle is decreased bellow the critical temperature for installed devices and engine parts (gear box etc.) in this compartments. Using a 3D CFD model of the first compartment of the nacelle is analyzed using the software ANSYS. The boundary conditions for this CFD simulation are obtained from ground testing of the turboprop engine.

Copyright © 2018 by ASME



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