In helicopter turboshaft engines, turbine blades operate under severe thermal and mechanical conditions. As engine power increases, the gas temperature downstream of the combustion chamber can reach approximately 1300 K, while high rotational speeds generate significant centrifugal forces. In addition, blades are exposed to non-uniform thermal and aerodynamic loads from hot gas flow, which strongly affect material properties. This study presents a numerical investigation of the temperature distribution in first-stage turbine rotor blades without internal cooling channels. The results identify regions of maximum temperature and assess blade durability. Comparison between numerical and theoretical results shows small temperature deviations: about 30°C at the tip, 8°C at mid-span, and 15°C at the root.

Le Thanh Nguyen, Duc Dung Nguyen, The Son Nguyen, "Study on the Temperature Distribution in the First-Stage Turbine Blades of the TB3-117 Engine" International Journal of Advanced Multidisciplinary Research and Educational Development, V2(1): Page(907-911) Jan-Feb 2026. ISSN: 3107-6513. www.ijamred.com. Published by Scientific and Academic Research Publishing.