초록 ▼

A method and system for detecting damage to the rotor of an aircraft engine using devices for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method includes the follo

A method and system for detecting damage to the rotor of an aircraft engine using devices for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method includes the following steps: reading the acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of the acquired data; calculating a vector difference between the mean vibration vector of the determined flight and the mean vibration vector of a reference flight for the rotor speed range; comparing the modulus of the vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of the vector difference exceeds the predetermined threshold value, the steps being performed after the determined flight has been completed.

대표청구항 ▼

1. A method of detecting damage to the rotor of an aircraft engine including means for measuring vibration and speed in order to acquire data relating to rotor speed and to the amplitude and the phase of rotor vibrations during a determined flight, the method comprising the following steps:reading s

1. A method of detecting damage to the rotor of an aircraft engine including means for measuring vibration and speed in order to acquire data relating to rotor speed and to the amplitude and the phase of rotor vibrations during a determined flight, the method comprising the following steps:reading said acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data, the determined rotor speed range corresponding to a value of 1 to 10% of a nominal speed of the rotor; for said rotor speed range, calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight; comparing the modulus of said vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of said vector difference exceeds said predetermined threshold value; wherein said steps are performed after said determined flight has been completed. 2. A detection method according to claim 1, further comprising the following steps:for said rotor speed range, calculating a second vector difference between each vibration vector of said determined flight and the mean vibration vector of a reference flight; calculating the modulus of said second vector difference associated with each vibration vector in order to select the maximum modulus; comparing said maximum modulus with the predetermined threshold value; and issuing a warning signal when said maximum modulus exceeds the predetermined threshold value. 3. A detection method according to claim 1, further comprising the following steps:for said rotor speed range, calculating a third vector difference between each vibration vector of said determined flight and the mean vibration vector of said determined flight; calculating a modulus for said third vector difference associated with each vibration vector in order to select a maximum modulus; comparing said maximum modulus with the predetermined threshold value; and issuing a warning signal when said maximum modulus exceeds the predetermined threshold value. 4. A detection method according to claim 1, wherein the reference flight corresponds to the flight preceding said determined flight.5. A detection method according to claim 1, wherein the reference flight corresponds to a flight associated with a standard, reference engine.6. A detection method according to claim 1, further comprising a step of updating the mean vectors of the reference flight from the data of said determined flight whenever the modulus or the maximum modulus of the vector difference does not exceed the predetermined threshold value.7. A detection method according to claim 1, wherein the threshold value is determined depending on the location of the vibration detection means and correspond to a value lying in the range 2 mils to 5 mils.8. A computer program on a tangible computer readable medium, comprising: a first computer code configured to implement the method according to claim 1 when executed by a computer.9. A system for detecting damage to the rotor of an aircraft engine provided with vibration measurement means and speed measurement means for acquiring data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight, the system comprising:means for reading said acquired data; means for calculating vibration vectors as a function of rotor speed; means for calculating a plurality of rotor speed ranges on the basis of said acquired data; means for calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data, the determined rotor speed range corresponding to a value of 1 to 10% of a nominal speed of the rotor; means for calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; means for comparing the modulus of said vector difference with a predetermined threshold value; means for issuing a warning signal when said modulus of said vector difference exceeds said predetermined threshold value; and storage means for storing said data relating to the speed, the amplitude, and the phase of vibration of the rotor to enable them to be processed after said determined flight has been completed. 10. A detection system according to claim 9, further comprising:means for calculating a second difference between each vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; means for calculating a modulus for said second vector difference associated with each vibration vector and for selecting the maximum modulus; means for comparing said maximum modulus with the predetermined threshold value; and means for issuing a warning signal when said maximum modulus exceeds the predetermined threshold value. 11. A detection system according to claim 9, further comprising:means for calculating a third vector difference between each vibration vector of said determined flight and the mean vibration vector of said determined flight for said rotor speed range; means for calculating a modulus of said third vector difference associated with each vibration vector in order to select a maximum modulus; means for comparing said maximum modulus with the predetermined threshold value; and means for issuing a warning signal when said maximum modulus exceeds the predetermined threshold value. 12. A detection system according to claim 9, including at least one means for measuring vibration in a radial plane of the engine.13. An aircraft engine comprising a compressor fitted with first rotary disks and a turbine fitted with second rotary disks, the engine including a detection system according to claim 9.14. An aircraft engine according to claim 13, wherein the detection system comprises first vibration measurement means at one of the first rotary disks and second vibration measurement means at the second rotary disks.15. A system for detecting damage to a rotor of an aircraft engine, comprising:a vibration instrument configured to make a plurality of rotor vibration measurements during a flight of an airplane equipped with the aircraft engine, each measurement of the plurality of rotor vibration measurements comprising an amplitude and a phase; a rotor speed instrument configured to make a plurality of rotor speed measurements; and a data processor unit configured to acquire the plurality of rotor vibration and rotor speed measurements from the respective vibration and rotor speed instruments, to calculate a plurality of rotor speed ranges, to calculate vibration vectors as a function of rotor speed and a mean vibration vector for each speed range of the plurality, to calculate, for each speed range of the plurality, a vector difference between the mean vibration vector calculated during the flight and a mean vibration vector of a reference flight, to compare a modulus of the vector difference with a predetermined threshold value, and to issue a warning signal when the modulus of the vector difference exceeds the predetermined threshold value. 16. The system according to claim 15, wherein the data processor system is further configured to store the rotor vibration and rotor speed measurements in a memory and to perform data processor system calculations after completion of the flight.17. The system according to claim 15, wherein the rotor speed instrument further comprises:a first compressor rotor speed instrument; and a first turbine rotor speed instrument. 18. The system according to claim 15, wherein, for rotor speeds between 80 to 110% of the nominal speed of the rotor, the rotor speed ranges of the plurality correspond to a value of 1% of the nominal speed of the rotor.19. The system according to claim 15, wherein rotor speed ranges for rotor speeds less than 80% of the nominal speed of the rotor correspond to 2% or more of the nominal speed and rotor speed ranges are not calculated for rotor speeds below 20% of the nominal speed of the rotor.20. The system according to claim 15, wherein each rotor speed range of the plurality corresponds to a value of 1 to 10% of a nominal speed of the rotor.21. The system according to claim 15, wherein the vibration vectors are parameterized as a function of rotor speed.22. The system according to claim 15, wherein the speed ranges of the plurality are divided in non-regular subdivisions.