HEAT TRANSFER ANALYSIS OF DAMAGED SHROUDED HIGH-PRESSURE TURBINE ROTOR BLADES

Carta M.;Ghisu T.;Shahpar S.

2023-01-01

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Abstract

Due to the increasingly high turbine inlet temperatures, heat transfer analysis is now more than ever a vital part of the design and optimization of high-pressure turbine rotor blades of a modern jet engine. The present study aims to find-out how shape deviation and in-service deterioration affect heat exchange patterns on the rotor blade. The rotor geometries used for this analysis are represented by a set of high-resolution 3D structured light scans of blades with the same number of in-service hours. An automatic meshing technique is employed to generate high-resolution meshes directly on the scanned rotor geometries, which allows to capture all the surface features with high fidelity. Steady-state 3D RANS flow simulations with k-ω SST turbulence model were conducted on a one-and-a-half stage computational domain of the scanned geometries. First, the distribution of heat transfer coefficient is calculated for each blade, then, a correlation is sought between heat transfer coefficient and parametrized shape deviation.