Abstract: A method of determining a turbine inlet temperature for a gas turbine engine includes measuring pressure changes within a combustion section of the gas turbine engine during operation of the gas turbine engine to produce pressure versus time data, extracting a resonant frequency from the pressure versus time data, and calculating the turbine inlet temperature based solely on the resonant frequency.

Abstract: A method of determining a turbine inlet temperature for a gas turbine engine includes measuring pressure changes within a combustion section of the gas turbine engine during operation of the gas turbine engine to produce pressure versus time data, extracting a resonant frequency from the pressure versus time data, and calculating the turbine inlet temperature based solely on the resonant frequency.

Abstract: The state of a flame in a gas turbine engine combustor is acoustically monitored using a dynamic pressure sensor within the combustor. A spectral pattern of a dynamic pressure sensor output signal from the sensor is compared with a characteristic frequency pattern that includes information about an acoustic pattern of the flame and information about acoustic signal canceling due to reflections within the combustor. The spectral pattern may also be compared with a characteristic frequency pattern including information about a flame-out condition in the combustor.

Abstract: The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors. The cross correlation may be constrained by a maximum time delay between correlated components of the signals, based on physical characteristics.

Abstract: The flame status of a group of gas turbine combustors is acoustically monitored using dynamic pressure sensors within the combustor. Dynamic pressure sensor output signals are received from the sensors and processed to determine flame status. The signals are processed both by performing a correlation analysis within each combustor and by applying a wavelet-based flame detection algorithm to each output signal. A flame is determined to be present based on the correlation analysis and the wavelet-based flame detection algorithm. The wavelet-based flame detection algorithm is chosen based on whether the gas turbine combustors are in an ignition phase or a monitoring phase.

Abstract: The state of a flame in a gas turbine combustor is acoustically monitored using a single dynamic pressure sensor within the combustor. A dynamic pressure sensor output signal is received from the single sensor and is processed to determine a flame status. The signal is processed by performing an autocorrelation operation to identify time-separated portions of the signal and to determine that the time-separated portions of the signal include portions indicative of acoustic oscillations emitted by the flame in the gas turbine engine combustor and received directly by the single acoustic sensor, and portions indicative of reflections.

Abstract: The flame status of a group of gas turbine combustors is acoustically monitored using dynamic pressure sensors within the combustor. Dynamic pressure sensor output signals are received from the sensors and processed to determine flame status. The signals are processed both by performing a correlation analysis within each combustor and by applying a wavelet-based flame detection algorithm to each output signal. A flame is determined to be present based on the correlation analysis and the wavelet-based flame detection algorithm. The wavelet-based flame detection algorithm is chosen based on whether the gas turbine combustors are in an ignition phase or a monitoring phase.

Abstract: The state of a flame in a gas turbine combustor is acoustically monitored using a single dynamic pressure sensor within the combustor. A dynamic pressure sensor output signal is received from the single sensor and is processed to determine a flame status. The signal is processed by performing an autocorrelation operation to identify time-separated portions of the signal and to determine that the time-separated portions of the signal include portions indicative of acoustic oscillations emitted by the flame in the gas turbine engine combustor and received directly by the single acoustic sensor, and portions indicative of reflections.

Abstract: The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors. The cross correlation may be constrained by a maximum time delay between correlated components of the signals, based on physical characteristics.

Abstract: The state of a flame in a gas turbine engine combustor is acoustically monitored using a dynamic pressure sensor within the combustor. A spectral pattern of a dynamic pressure sensor output signal from the sensor is compared with a characteristic frequency pattern that includes information about an acoustic pattern of the flame and information about acoustic signal canceling due to reflections within the combustor. The spectral pattern may also be compared with a characteristic frequency pattern including information about a flame-out condition in the combustor.