Abstract
Ice ingestion can lead to a range of detrimental effects, from diminished engine performance to potentially catastrophic failure, especially for first compressor stages. As the ice is traveling through the engine, the impact with engine components that rotate at high speed can result in severe mechanical damage. The blades leading edge in the low-pressure compressor are particularly prone to local damage. Therefore, it is important to consider ice impact simulations as soon as possible in the design process. In this context, the authors propose a multi-disciplinary surrogate-based optimization strategy for a compressor rotor that includes ice impact simulations. For this purpose, a dedicated 3D blade parametrization is first introduced. Then, based on this set of parameters, the proposed optimization chain is presented and each chain block is detailed. In particular, aerodynamical simulations are considered at three flight conditions, maximum static stresses and frequency margins with respect to specific engine orders are evaluated, blade robustness to blade/casing contact events is assessed using the clearance consumption simplified criteria, and ice impact simulations are carried out using transient response computations with an explicit time integration scheme and the ice fragment modeled with the SPH method. A dedicated lower-fidelity model has been developed for the purpose of optimization loops to maintain reasonable computations times. The proposed strategy is applied to design a rotor blade of a low-pressure compressor. The aim is to satisfy all mechanical constraints to ensure the blade robustness in operation, without deteriorating its aerodynamic performance.
