Method and system for determining the flow rate of air collected from an aircraft engine

1. A method for monitoring an aircraft engine by determining, in real time, flow rate of air collected from a high-pressure compressor of the aircraft engine by an air collection system of the aircraft engine, the method comprising:

acquiring at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for the air collection system, the acquiring at the successive times the measurements of the physical quantities comprising collecting data from a first sensor between an engine anti-ice nacelle and a nacelle anti-ice valve, a second sensor between the high-pressure compressor and a pressure shut-off valve, a pair of third differential pressure sensors between the pressure shut-off valve and an output of precooler, and a plurality of temperature sensors between the precooler and a bleed air shut-off valve;

evaluating at each current time of said successive times of a first current air flow rate estimation of air collected from the high-pressure compressor of the aircraft engine on the basis of said physical quantity measurements;

acquiring at a current time of said successive times a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables and according to an aircraft altitude;

selecting at said current time said first current air flow rate estimation or said minimum current air flow rate data item to form a second current air flow rate estimation, the selection being made on the basis of a degree of precision of each of the first current air flow rate estimation and the minimum current air flow rate data; and

adjusting a current fuel rate threshold value of the aircraft engine based on the first current air flow rate estimation or the second current air flow rate estimation to correct acceleration stop of the aircraft engine.

2. The method according to claim 1 , wherein said selecting comprises selecting the greatest value between said first current air flow rate estimation and said minimum current air flow rate data item.

3. The method according to claim 1 , further comprising:

determining at said current time a third current air flow rate estimation by increasing said second current air flow rate estimation by an additional current anti-ice nacelle air flow rate value collected from the engine; and

adjusting the current fuel rate threshold value of the aircraft engine based on the first current air flow rate estimation or the second current air flow rate estimation or the third current air flow rate estimation.

4. The method according to claim 1 , further comprising verifying non-deviant nature of said physical quantity measurements before evaluating said first current air flow rate estimation.

5. The method according to claim 1 , wherein evaluating said first current air flow rate estimation comprises:

computing said current time an intermediate current air flow rate estimation of the flow rate of air collected from the high-pressure compressor of the aircraft engine on the basis of said physical quantity measurements,

computing said current time a current flow rate error induced by uncertainties in respect of said physical quantity measurements, and

correcting said current time said intermediate current flow rate estimation by subtracting therefrom said current flow rate error thus determining said first current air flow rate estimation.

6. The method according to claim 1 , wherein the pressure loss is measured at terminals of a heat exchanger of said air collection system.

7. The method according to claim 1 , wherein said flow rate tables are air collection set-points for conditioning an aircraft cabin, and minimum current air flow rate data item is defined on the basis of a configuration selected in said flow rate tables and the aircraft altitude.

8. A device for monitoring an aircraft engine by determining, in real time, flow rate of air collected from a high-pressure compressor of the aircraft engine by an air collection system of the aircraft engine, the device comprising:

circuitry configured to

acquire at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for the air collection system, acquiring at the successive times the measurements of the physical quantities comprising collecting data from a first sensor between an engine anti-ice nacelle and a nacelle anti-ice valve, a second sensor between the high-pressure compressor and a pressure shut-off valve, a pair of third differential pressure sensors between the pressure shut-off valve and an output of precooler, and a plurality of temperature sensors between the precooler and a bleed air shut-off valve,

evaluate at each current time of said successive times a first current air flow rate estimation of air collected from the high-pressure compressor of the aircraft engine on the basis of said physical quantity measurements,

acquire at a current time of said successive times a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables and according to an aircraft altitude,

select, at said current time, said first current air flow rate estimation or said minimum current air flow rate data item to form a second current air flow rate estimation, the selection being made on the basis of a degree of precision of each of the first current air flow rate estimation and the minimum current air flow rate data, and

adjust a current fuel rate threshold value of the aircraft engine based on the first current air flow rate estimation or the second current air flow rate estimation to correct acceleration stop of the aircraft engine.

9. A non-transitory computer-readable storage medium including computer executable instructions, wherein the instructions, when executed by a computer, cause the computer to perform a method for monitoring an aircraft engine, the method comprising:

acquiring at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for an air collection system, the acquiring at the successive times the measurements of the physical quantities comprising collecting data from a first sensor between an engine anti-ice nacelle and a nacelle anti-ice valve, a second sensor between a high-pressure compressor and a pressure shut-off valve, a pair of third differential pressure sensors between the pressure shut-off valve and an output of precooler, and a plurality of temperature sensors between the precooler and a bleed air shut-off valve;

evaluating at each current time of said successive times of a first current air flow rate estimation of air collected from the high-pressure compressor of the aircraft engine on the basis of said physical quantity measurements;

acquiring at a current of said successive times time a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables and according to an aircraft altitude;

selecting at said current time said first current air flow rate estimation or said minimum current air flow rate data item to form a second current air flow rate estimation, the selection being made on the basis of a degree of precision of each of the first current air flow rate estimation and the minimum current air flow rate data; and

adjusting a current fuel rate threshold value of the aircraft engine based on the first current air flow rate estimation or the second current air flow rate estimation to correct acceleration stop of the aircraft engine.