Abstract: A method for determining a predictive model of a pressure ratio P1/P2 for a bypass turbomachine of previously defined type including primary and secondary air paths separated by an inter-path compartment, the P1 pressure corresponding to an air pressure inside the inter-path compartment, the P2 pressure corresponding to an air pressure in the secondary air path. The method includes acquiring, on a test turbomachine in operation, at respective measurement times, sets of measurements each including a P1 measurement, a P2 measurement, a measurement M of a Mach number of the test turbomachine, and a PCN12R measurement representing a low pressure rating, obtaining the sets of measurements by a processing device, supervised learning, by the processing device and on the basis of the sets of measurements obtained, of a predictive model of the ratio P1/P2 as a function of the M number and of the PCN12R rating considered as explanatory variables.

Abstract: A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.

Abstract: A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.