METHOD FOR THE PREDICTION OF SURGE IN A GAS COMPRESSOR

摘要

A computer implemented method (100) for the prediction of the surge point of a compressor (14) comprises the following steps: - generating (110) a plurality of meshes: - a compressor inlet mesh (220), - at least a compressor rotor stage mesh (225), - a compressor outlet mesh (235), representing a plurality of exit guide vanes (236) and an exit nozzle (37) and extending up to a final nozzle exit area (240), - assembling (120) the plurality of meshes (220, 225, 235) to obtain the CFD domain (250), - specifying boundary conditions (130) of the computational domain (250), - specifying atmospheric pressure conditions (140) at the final nozzle exit area (40), - computing (150) compressor inlet mass flow rate and compressor pressure ratio, - if the numerical stability limit is not reached then: - decreasing (180) dimensions (A1) of the final nozzle exit area (240), - generating again (190) the compressor outlet mesh (235), - repeating said steps of specifying atmospheric pressure (140) at the final nozzle exit area (240), said step of computing (150) and said step of checking (160).