Abstract In this paper we consider the impact of nozzle guide vane trailing edge burn-back (damage) on cooled high-pressure turbine stage performance. We analyse four levels of simulated burn-back ranging from new parts to severely damaged. The burn-back geometries are based on a statistical analysis of real deterioration data from operating engines. We use unsteady stage simulations to predict the impact of burn-back on capacity, reaction, specific work, and efficiency, among other performance metrics. For CFD validation, we use experimental data from the Engine Component Aero-Thermal (ECAT) facility at the University of Oxford. This is a full-annular nozzle guide vane cascade, operating at engine-matched conditions of Mach and Reynolds number. The overall purpose of this study is to improve understanding of the impact of burn-back on whole-life engine performance.
Raduev et al. (Thu,) studied this question.
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