Numerical simulation of ablative particle deposition on gas turbine blade based on gas-solid two-phase flow

The development of modern heavy-duty gas turbine technology has led to a gradual increase in combustion temperature. This increase has resulted in a higher incidence of gas turbine ablation failures. Ablation produces a large number of high-temperature particles that flow downstream with the gas and presents a safety hazard to gas turbine components and the stable operation of the gas turbine. This paper investigates the deposition behaviour of ablative particles of three different sizes on gas turbine blades through numerical simulation. The results indicate that the deposition rate is highest for 10μm particles on the stator blade pressure surface. The overall deposition rate on the dynamic blade pressure surface decreases, and the highest deposition rate is observed for 2.5μm particles.