A numerical simulation strategy for a compressor's underlying axisymmetric characteristic and its application in body force model

Accurate prediction of the aerodynamic response of a compressor under inlet distortion is crucial for next-generation civil aircraft, such as Boundary Layer Ingestion (BLI) silent aircraft. Therefore, research on the Body Force (BF) model plays a significant role in achieving this objective. However, distorted inlet airflow can lead to varying operating conditions across different spatial locations of the compressor, which may cause some regions to operate outside the stability boundary. Consequently, the accuracy of BF model simulations might be compromised. To address this issue, this paper proposes a numerical simulation strategy for acquiring the steady axisymmetric three-dimensional flow field of a compressor operating at low mass flow rates, which is known as the Underlying Axisymmetric Pressure Rise Characteristic (UAPRC). The proposed simulation accounts for two different rotor speeds of a transonic compressor and identifies initial positions in the flow field where deterioration occurs based on prior experimental investigations. Moreover, simulation results are incorporated into the BF model to replicate hub instability observed in experiments. Obtained results demonstrate that this strategy provides valid predictions of the UAPRC of the compressor, thereby addressing the limitations associated with the BF model.