Investigation of stall recovery potential in a transonic compressor rotor

Abstract

In order to evaluate the potential of stall recovery at different operating points during the stall process in a transonic environment, three-dimensional multi-passage numerical simulations were conducted on the transonic compressor, NASA Rotor 37. The results showed that the whole stall evolution process can be divided into three stages depending upon the possibility for the compressor to recover to a stable operating condition by reducing the outlet pressure. At the first stage of the stall process, the compressor could successfully be driven back to a stable operating state by decreasing the outlet pressure. In addition, it was observed that the time of the stall recovery process was shorter when the outlet pressure was lowered more. At the second stage of stall, the magnitude of the outlet pressure played a decisive role in determining whether the compressor could recover to a stable state. When the compressor operation moved to the third stage of the stall process, “stall hanging” occurred, which means that the compressor could not recover from the stall regardless of how much the outlet pressure was reduced.

An overall blockage attenuation-based aerodynamic performance and stability design optimization method for transonic axial flow compressors

“…The predicted overall pressure ratio matches the measured data fairly well, whereas the calculated adiabatic efficiency is underestimated slightly. This efficiency underestimation is consistent with the RANS-based results in published studies, such as the research (Bruna and Turner, 2013) conducted by NASA using ANSYS CFX and other recent studies (Xu et al , 2020; Wang et al , 2022; Lang et al , 2021). In addition, the near-stall point predicted based on unsteady simulation is very close to the experiment stall mass.…”