Abstract: A method for determining when a combustor is experiencing hardware damage includes sensing acoustic vibrations of a plurality of combustor cans, determining a center frequency for each acoustic tone of the sensed acoustic vibrations within a predetermined frequency range, and indicating an alarm when a center frequency of one or more of the combustor cans changes in a different manner compared to a representative center frequency of the plurality of combustor cans.

Abstract: A method for determining a lean blow out condition for a combustor. In an exemplary embodiment, the method includes determining acoustical frequency data for the combustor, determining a combustor flame temperature based on the acoustical frequency data, determining an existing fuel/air ratio in the combustor based on the combustor flame temperature, and comparing the existing fuel/ratio to a lean blow out fuel/air ratio. A lean blow out condition for the combustor is indicated when the existing fuel/air ratio is about equal to the lean blow out fuel/air ratio.

Abstract: Systems, methods and computer program products enable the remote monitoring of the combustion dynamics of turbines. Remote monitoring permits a single user to continuously monitor the operating health of a fleet of turbines simultaneously from a single location. The user is presented with one or more graphical user interfaces that graphically display combustion dynamics data to enable the user to visually and quickly determine whether the turbine is operating within prescribed limits. The system permits the user to determine whether each turbine is operating to its maximum efficiency.

Abstract: A method for monitoring and diagnosing the combustion dynamics of a gas turbine engine system includes mounting at least one sensor on an external surface of at least one combustor can, receiving a signal from the sensor mounted to the combustor can, validating an accuracy of the signal from the sensors, determining the combustion dynamics of the can based on the received signals, and generating an indication when a combustion dynamic threshold has been exceeded.

Abstract: A method of determining the temperature inside a combustion liner without making a direct measurement of the actual temperature. The technique is based on a measurement of the frequency of one of the transverse acoustic modes occurring inside the combustion chamber. The frequency is determined from the transverse geometric dimensions of the combustion chamber and the speed of sound in the gas inside the combustion chamber. The speed of sound in the gas is known from thermodynamics to be a function of gas temperature and gas properties. Thus, from a measurement of the resonant frequency and knowing the combustor dimensions and gas properties, the temperature can be determined with accuracy.

Abstract: A method of selectively controlling communication between a supervisory processor and a subscriber is provided. The method includes receiving a stream of data at the supervisory processor, controlling transmission of the stream of data from the supervisory processor to the subscriber based on an associated supervisory processor configuration, receiving an enabling configuration at the supervisory processor which alters the supervisory processor configuration, and transmitting at least a portion of the controlled stream of data from the supervisory processor to the subscriber based on the supervisory processor configuration.

Abstract: In one embodiment, the invention is a pressure sensor calibration system comprising a pressure chamber in fluid communication with a pressure sensor to be calibrated, the chamber is pressurized to a static pressure level. An oscillating surface on a wall of the chamber imparts a rapid pressure fluctuation in the static pressure level of the chamber. These rapid pressure fluctuations in a high-static pressure level chamber are used to calibrate the pressure sensor.

Abstract: In one embodiment, the invention is a pressure sensor calibration system comprising a pressure chamber in fluid communication with a pressure sensor to be calibrated, the chamber is pressurized to a static pressure level. An oscillating surface on a wall of the chamber imparts a rapid pressure fluctuation in the static pressure level of the chamber. These rapid pressure fluctuations in a high-static pressure level chamber are used to calibrate the pressure sensor.

Abstract: A method for monitoring and diagnosing the combustion dynamics of a gas turbine engine system includes mounting at least one sensor on an external surface of at least one combustor can, receiving a signal from the sensor mounted to the combustor can, validating an accuracy of the signal from the sensors, determining the combustion dynamics of the can based on the received signals, and generating an indication when a combustion dynamic threshold has been exceeded.

Abstract: In one embodiment, the invention is a pressure sensor calibration system comprising a pressure chamber in fluid communication with a pressure sensor to be calibrated, the chamber is pressurized to a static pressure level. An oscillating surface on a wall of the chamber imparts a rapid pressure fluctuation in the static pressure level of the chamber. These rapid pressure fluctuations in a high-static pressure level chamber are used to calibrate the pressure sensor.