Author:
Pařez Jan,Tater Adam,Polanský Jiří,Vampola Tomáš
Abstract
Presented paper is focused on numerical simulation of turboprop engine cooling in the section of a gas turbine. The method of heat transfer motor cooling by natural convection and radiation is described. The heat transfer in gas turbine section is represented on a simplified double annular geometry. Numerical data were compared with data that was gained from measuring on an experimental stand. The surface temperatures of the tubes were measured on the experiment stand during the cooling of the engine model. Numerical and experimental results reach a good agreement and will be further applied to the study of temperature-dependent deformation of aircraft engine parts, which have a significant effect on the safety and flawless operation of the aircraft engine.
Cited by
1 articles.
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