Systems and methods for monitoring aerostructures are provided. In various embodiments, a method for monitoring an aerostructure may include: receiving a signal from a pressure sensor, the pressure sensor located downstream from the aerostructure; performing a time frequency analysis on the signal t
Systems and methods for monitoring aerostructures are provided. In various embodiments, a method for monitoring an aerostructure may include: receiving a signal from a pressure sensor, the pressure sensor located downstream from the aerostructure; performing a time frequency analysis on the signal to calculate a power level over a range of frequencies; monitoring the power level over the range of frequencies; and determining a susceptibility to a flutter condition based on the monitoring the power level.
대표청구항▼
1. A method for monitoring fan blades for a gas turbine engine comprising: receiving, by a controller, a signal from a pressure sensor, the pressure sensor located downstream from the fan blades;performing, by the controller, a time frequency analysis on the signal to calculate a power level over a
1. A method for monitoring fan blades for a gas turbine engine comprising: receiving, by a controller, a signal from a pressure sensor, the pressure sensor located downstream from the fan blades;performing, by the controller, a time frequency analysis on the signal to calculate a power level over a range of frequencies of the signal;monitoring, by the controller, the power level over the range of frequencies;determining a shift in the power level from a lower frequency to a higher frequency; anddetermining, by the controller, a susceptibility to a flutter condition based on the shift in the power level. 2. The method of claim 1, wherein the pressure sensor is capable of measuring a dynamic frequency with a Nyquist frequency greater than at least a third fundamental frequency of the fan blades. 3. The method of claim 1, wherein the performing the time frequency analysis includes at least one of performing a Fourier transform, a wavelet transform, a bilinear time frequency distribution, or a modified Wigner distribution function. 4. The method of claim 1, wherein the monitoring the power level includes calculating a change in the power level over the range of frequencies. 5. The method of claim 4, wherein the monitoring the power level includes calculating the change in the power level at a pre-determined frequency. 6. The method of claim 1, wherein the determining the susceptibility to the flutter condition is based on the power level over the range of frequencies. 7. The method of claim 6, wherein the determining the susceptibility to the flutter condition includes determining if the power level is above a threshold value. 8. The method of claim 6, wherein the determining the susceptibility to the flutter condition includes determining a shift in the power level from a lower frequency to a higher frequency. 9. A method for monitoring fan blades for a gas turbine engine, comprising: receiving, by a controller, a signal from a pressure sensor, the pressure sensor located downstream from the fan blades;calculating, by the controller, a first bandpass signal based on the signal;calculating, by the controller, a second bandpass signal based on the signal, the second bandpass signal comprising a higher frequency than the first bandpass signal;performing, by the controller, a time frequency analysis on the first bandpass signal and the second bandpass signal to calculate a first power level of the first bandpass signal and a second power level of the second bandpass signal; anddetermining, by the controller, a change in at least one of a magnitude of the first power level and a magnitude of the second power level. 10. The method of claim 9, further comprising, determining, by the controller, a susceptibility to a flutter condition based on at least one of the first power level and the second power level. 11. The method of claim 10, further comprising, outputting, by the controller, an indicating signal based on the determining the susceptibility, the indicating signal indicating the susceptibility. 12. The method of claim 9, wherein the pressure sensor is capable of measuring a dynamic frequency with a Nyquist frequency greater than at least a third fundamental frequency of the fan blades. 13. The method of claim 9, wherein the performing the time frequency analysis includes at least one of performing a Fourier transform, a wavelet transform, a bilinear time frequency distribution, or a modified Wigner distribution function. 14. The method of claim 9, wherein the determining the change includes determining a shift in the magnitude of the first power level to the magnitude of the second power level. 15. A system for monitoring fan blades for a gas turbine engine, comprising: a pressure sensor configured to be located downstream from the fan blades;a controller in electronic communication with the pressure sensor; anda tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising: receiving, by the controller, a signal from the pressure sensor;performing, by the controller, a time frequency analysis on the signal to calculate a power level over a range of frequencies of the signal;monitoring, by the controller, the power level over the range of frequencies;determining a shift in the power level from a lower frequency to a higher frequency; andoutputting an indicating signal based on the shift in the power level. 16. The system for monitoring fan blades of claim 15, wherein the indicating signal indicates a susceptibility to a flutter condition of the aerostructure. 17. The system for monitoring fan blades of claim 15, wherein the instructions cause the controller to perform operations further comprising: calculating a first bandpass signal based on the signal;calculating a second bandpass signal based on the signal, the second bandpass signal comprising a higher frequency than the first bandpass signal;performing the time frequency analysis on the first bandpass signal and the second bandpass signal to calculate a first power level of the first bandpass signal and a second power level of the second bandpass signal; anddetermining a change in at least one of a magnitude of the first power level and a magnitude of the second power level. 18. The system for monitoring fan blades of claim 15, wherein the pressure sensor is capable of measuring a dynamic frequency with a Nyquist frequency greater than at least a third fundamental frequency of the aerostructure. 19. The system for monitoring fan blades of claim 18, wherein the pressure sensor is configured to be coupled to at least one of an inner fixed structure or a fan case.
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이 특허에 인용된 특허 (2)
Gysling Daniel L. ; Feulner Matthew R. ; Eveker Kevin M., Apparatus and method of active flutter control.
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