Abstract: A gas turbine and a method for operating a gas turbine having a fuel gas monitoring system are presented. The fuel gas monitoring system may provide a measurement of a parameter of a fuel gas in real time. An operation of a gas turbine may be optimized to adapt variation in hydrocarbon content of a fuel gas from the measurement. The fuel gas monitoring system may provide an optical, flow through, online monitoring of fuel gas composition.

Abstract: A method for measuring air mass flow into a compressor section of a gas turbine engine is provided. Air is introduced into a chamber upstream from an inlet of the compressor section. The chamber includes filter packages with at least some of the filter packages including a flow sensor and a filter structure, the filter structure filtering the air. The flow sensors measure the velocity of the air flowing through the corresponding filter package. A controller uses the air flow sensor signal data to characterize a two dimensional flow field through the chamber. Additionally, a plurality of temperature, humidity, and static pressure sensors are disposed throughout the filter packages. The controller uses the temperature, humidity, and static pressure sensor signal data to characterize a two dimensional density field through the chamber. The controller combines the flow field with the density field to calculate a two dimensional air mass flow field.

Abstract: A method for measuring air mass flow into a compressor section of a gas turbine engine is provided. Air is introduced into a chamber upstream from an inlet of the compressor section. The chamber includes filter packages with at least some of the filter packages including a flow sensor and a filter structure, the filter structure filtering the air. The flow sensors measure the velocity of the air flowing through the corresponding filter package. A controller uses the air flow sensor signal data to characterize a two dimensional flow field through the chamber. Additionally, a plurality of temperature, humidity, and static pressure sensors are disposed throughout the filter packages. The controller uses the temperature, humidity, and static pressure sensor signal data to characterize a two dimensional density field through the chamber. The controller combines the flow field with the density field to calculate a two dimensional air mass flow field.

Abstract: A self validating flame detection system (10) for a turbine engine (12) configured to determine whether a flame exists in a turbine engine combustor is disclosed. The self validating flame detection system (10) may include two different types of flame detection sensors to reduce the risk of false positive signals. In at least one embodiment, the flame detection system (10) may include one or more infrared sensors (20) that sense infrared radiation within the combustor of the turbine engine (12) and one or more ultraviolet light sensors (22) that sense ultraviolet light within the combustor of the turbine engine (12). The flame detection system (10) may include a processor (24) configured to ignore the steady state infrared signal generated and instead analyze the dynamic infrared signal. The processor (24) may be configured to determine whether both types of sensors indicate a flame out condition so that a false alarm does not occur.

Abstract: A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

Abstract: A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

Abstract: A self validating flame detection system (10) for a turbine engine (12) configured to determine whether a flame exists in a turbine engine combustor is disclosed. The self validating flame detection system (10) may include two different types of flame detection sensors to reduce the risk of false positive signals. In at least one embodiment, the flame detection system (10) may include one or more infrared sensors (20) that sense infrared radiation within the combustor of the turbine engine (12) and one or more ultraviolet light sensors (22) that sense ultraviolet light within the combustor of the turbine engine (12). The flame detection system (10) may include a processor (24) configured to ignore the steady state infrared signal generated and instead analyze the dynamic infrared signal. The processor (24) may be configured to determine whether both types of sensors indicate a flame out condition so that a false alarm does not occur.

Abstract: A method and system for monitoring a gas turbine engine (20) to predict maintenance requirements. Particles suspended in a gas flow (24, 32) of the engine (20) are monitored and quantified to predict a particle accumulation rate. Monitoring may be done using particle flow sensors (61-63) in a diverted portion (33) of the working gas flow (24), such as in the cooling gas flow (32). Particle sampling (S1-S3) may be done to determine particle size and composition distributions. Particle mass flow rates may then be continuously monitored per engine operating condition, and compared to predetermined values such as a normal upper limit per engine operating condition. An integrated particle mass flow may be used in conjunction with an instantaneous mass flow rate to predict a maintenance requirement. Multiple locations (L1-L3) may be monitored to recognize a maintenance requirement by flow section or component.

Abstract: Aspects of the invention are directed to the use of microelectromechanical systems (MEMS) based emissions sensors in a turbine engine system to measure one or more emissions values associated with a gas flow in the system. The emissions value can be, for example, the temperature of a gas flow and/or the amount of a particular compound, such as carbon monoxide, in the gas flow. Due to their small size, a plurality of MEMS emissions sensors can readily be incorporated at various locations in a turbine engine system. For example, the MEMS emissions sensors can be operatively positioned in an exhaust stack, downstream of the last row of blades in the turbine section, or in the leading edge of a turbine vane. The MEMS sensors can be operatively connected to a data acquisition system, which can statistically analyze the emissions values measured by the MEMS sensors.

Abstract: Aspects of the invention are directed to the use of microelectromechanical systems (MEMS) based emissions sensors in a turbine engine system to measure one or more emissions values associated with a gas flow in the system. The emissions value can be, for example, the temperature of a gas flow and/or the amount of a particular compound, such as carbon monoxide, in the gas flow. Due to their small size, a plurality of MEMS emissions sensors can readily be incorporated at various locations in a turbine engine system. For example, the MEMS emissions sensors can be operatively positioned in an exhaust stack, downstream of the last row of blades in the turbine section, or in the leading edge of a turbine vane. The MEMS sensors can be operatively connected to a data acquisition system, which can statistically analyze the emissions values measured by the MEMS sensors.

Abstract: A method and system for monitoring a gas turbine engine (20) to predict maintenance requirements. Particles suspended in a gas flow (24, 32) of the engine (20) are monitored and quantified to predict a particle accumulation rate. Monitoring may be done using particle flow sensors (61-63) in a diverted portion (33) of the working gas flow (24), such as in the cooling gas flow (32). Particle sampling (S1-S3) may be done to determine particle size and composition distributions. Particle mass flow rates may then be continuously monitored per engine operating condition, and compared to predetermined values such as a normal upper limit per engine operating condition. An integrated particle mass flow may be used in conjunction with an instantaneous mass flow rate to predict a maintenance requirement. Multiple locations (L1-L3) may be monitored to recognize a maintenance requirement by flow section or component.