Patent ID: 11187235

Abstract:
A computer implemented method for the prediction of the surge point of a compressor includes: generating a plurality of meshes: a compressor inlet mesh, at least a compressor rotor stage mesh, and a compressor outlet mesh, representing a plurality of exit guide vanes and an exit nozzle and extending up to a final nozzle exit area; assembling the plurality of meshes to obtain the CFD domain; specifying boundary conditions of the computational domain; specifying atmospheric pressure conditions at the final nozzle exit area; computing compressor inlet mass flow rate and compressor pressure ratio; checking if the numerical stability limit is not reached, as a result of the numerical stability limit not being reached: decreasing dimensions of the final nozzle exit area; generating again the compressor outlet mesh; repeating the steps of specifying atmospheric pressure at the final nozzle exit area, the step of computing, and the step of checking.