Abstract: A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.

Abstract: The present intention relates to a method for resetting the static pressure model (mod_Ps3(PCN25R)), called “Ps3 model”, upstream of a combustion chamber in a turbine engine comprising a compressor (3), the Ps3 model being used to arbitrate between two acquisition channels (V10, V20) of the static pressure (Ps3), called “Ps3 pressure”, upstream of the combustion chamber, the two acquisition channels (V10, V20) using two sensors (10, 20), the model expressing the pressure Ps3 as a function at least of the speed (PCN25R), called “PCN25R speed”, of the compressor (3), and comprising the following steps: E1: measuring a value of the pressure Ps3 using one of the two sensors (10, 20); E2: resetting the Ps3 model using the measurement of the value of Ps3.

Abstract: A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.