Abstract: A gas turbine system and a method for controlling combustion instability in a combustion section of a gas turbine system are disclosed. The gas turbine system includes a compressor section, a turbine section connected to the compressor section, and a combustor section connected to the compressor section and the turbine section. The combustor section includes a plurality of combustors. The combustor section further includes at least one igniter for igniting a fuel-air mixture within each of the plurality of combustors into a hot gas. The gas turbine system further includes a control system for controlling a velocity of the hot gas in at least one of the plurality of combustors by controlling an operating parameter of the fuel-air mixture.

Abstract: In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for the supplied fuel to be ignited. In one aspect, fuel parameters related to the molecular weight of the fuel such as specific gravity and pressure drop are determined. Ignitability of the fuel is calculated based on the fuel parameters and adjusted as necessary to bring the fuel's ignitability to designed values. The fuel's ignitability can be calculated without actually igniting the fuel and also without direct knowledge of the fuel's calorific value or its composition.

Abstract: A system for operating a combustor includes a nozzle and a fuel passage and air passage through the nozzle. A fuel supply is in fluid communication with the fuel inlet, and an air supply is in fluid communication with the air inlet and the fuel inlet. A method for operating a combustor includes flowing a fuel through a fuel inlet in a nozzle and flowing air through an air inlet in the nozzle. The method further includes sensing an operating parameter of the combustor, generating a signal reflective of the operating parameter, and controlling a flow of at least one of air or diluent to the fuel inlet based on the signal reflective of the operating parameter.

Abstract: A system for operating a combustor includes a nozzle and a fuel passage and diluent passage through the nozzle. A fuel supply is in fluid communication with the fuel inlet, and a diluent supply is in fluid communication with the diluent inlet and the fuel inlet. A method for operating a combustor includes flowing a fuel through a fuel inlet in a nozzle and flowing a diluent through a diluent inlet in the nozzle. The method further includes sensing an operating parameter of the combustor, generating a signal reflective of the operating parameter, and controlling a flow of at least one of air or diluent to the fuel inlet based on the signal reflective of the operating parameter.

Abstract: A system for operating a combustor includes a nozzle and a fuel passage and diluent passage through the nozzle. A fuel supply is in fluid communication with the fuel inlet and the diluent inlet, and a diluent supply is in fluid communication with the diluent inlet. A method for operating a combustor includes flowing a fuel through a fuel inlet in a nozzle and flowing a diluent through a diluent inlet in the nozzle. The method further includes sensing an operating parameter of the combustor, generating a signal reflective of the operating parameter, and controlling a flow of the fuel to the diluent inlet based on the signal reflective of the operating parameter.

Abstract: Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

Abstract: A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.

Abstract: In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for the supplied fuel to be ignited. In one aspect, fuel parameters related to the molecular weight of the fuel such as specific gravity and pressure drop are determined. Ignitability of the fuel is calculated based on the fuel parameters and adjusted as necessary to bring the fuel's ignitability to designed values. The fuel's ignitability can be calculated without actually igniting the fuel and also without direct knowledge of the fuel's calorific value or its composition.

Abstract: The described method and system utilize continuous and/or periodic measurement of the fuel pipes to detect leakage of fuel. In general, the piping is enclosed in an air-tight containment cover so that a passage is formed between the piping and containment cover. Measurements can be conducted, using known hydrocarbon and other combustible gases industrial analyzers, and leak detectors. Pressure drop within the passage can be compensated by controlling of air inlet flow into the passage, coordinated with the analyzer pumping rate. Temperature and motion of a gas sample can be controlled by heating the inlet air. The system can includes the controlling valves for the leak source localization. The described method and system can be used to analyze and control fuel leak for late lean injection system for combustor of a turbine.

Abstract: In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for sustainable combustion during various stages of the turbine operation. In one aspect, combustible lean limit operation of the gas turbine free of lean blow out is enabled by adjusting fuel-air-ratio of the fuel and fuel-air mixture properties, based on the operation requirements of the turbine and flammability of the fuel components.

Abstract: A combined cycle power plant includes a compressor, a first turbine, a second turbine, a first combustor, a second combustor, a heat exchanger and a heat recovery steam generator. A controller operates the combined cycle power plant a first mode wherein compressor air is passed through the heat exchanger before being delivered to the first and second combustors, and exhaust gas from the second turbine is passed to the heat exchanger. The exhaust gas from the second turbine pre-heats the compressor air passing through the heat exchanger to the first and second combustors.

Abstract: A combined cycle power plant includes a compressor, a first turbine, a second turbine, a first combustor, a second combustor, a heat exchanger and a heat recovery steam generator. A controller operates the combined cycle power plant a first mode wherein compressor air is passed through the heat exchanger before being delivered to the first and second combustors, and exhaust gas from the second turbine is passed to the heat exchanger. The exhaust gas from the second turbine pre-heats the compressor air passing through the heat exchanger to the first and second combustors.

Abstract: A turbine engine includes a compressor, a combustor fluidly connected to the compressor and a first turbine operated by a combustion product formed in the first combustor. The turbine engine also includes a reheat chamber in which air, fuel, and exhaust gases from the first turbine are ignited to form a combustion product used to drive a second turbine. The engine further includes a controller that regulates at least one of an amount of fuel and compressed air delivered to the combustor and an amount of fuel, compressed air and exhaust gases delivered to the reheat chamber based on at least one turbine engine parameter measured by a sensor.

Abstract: A method and system for operating at partial load a gas turbine system having a compressor, a combustor, and a turbine. The method and system may include the steps of lowering a flow of fuel to the combustor, extracting air from the compressor so as to lower a flow of air to the compressor, and returning the extracted air to the turbine or a component of the gas turbine system other than the combustor. Extracting air from the compressor raises a combustion temperature within the combustor. Raising the combustion temperature maintains a combustion exhaust below a predetermined level, maintains stable combustion, and extends turbine turndown values.

Abstract: A blade tip clearance probe holder including: a first housing in operable communication with a first feature of a casing for a rotary machine; a spring rod assembly in operable communication with the first housing; an electrical capacitance clearance meter in operable communication with the spring rod assembly; and a second housing in operable communication with the first housing wherein the second housing initiates a preload on the spring rod assembly and wherein the electrical capacitance clearance meter maintains a constant spatial relationship with a second feature of the casing for the rotary machine.

Abstract: A blade tip clearance probe holder including: a first housing in operable communication with a first feature of a casing for a rotary machine; a spring rod assembly in operable communication with the first housing; an electrical capacitance clearance meter in operable communication with the spring rod assembly; and a second housing in operable communication with the first housing wherein the second housing initiates a preload on the spring rod assembly and wherein the electrical capacitance clearance meter maintains a constant spatial relationship with a second feature of the casing for the rotary machine.

Abstract: The fuel injector includes a solid state actuator that operates through an actuator motion amplifying lever to directly control the needle valve motion. Hydraulic forces, which act along the axes of the needle valve and the motion amplifying lever, are compensated by using a control piston, or other biasing means, to reduce the required amplitude of the control current/voltage and to reduce the required strength of the spring biasing the needle valve closed. The fuel injector may also include a control fuel inlet that is separate from the injection fuel inlet port.

Abstract: The fuel injector includes a solid state actuator that operates through an actuator motion amplifying lever to directly control the needle valve motion. Hydraulic forces, which act along the axes of the needle valve and the motion amplifying lever, are compensated by using a control piston, or other biasing means, to reduce the required amplitude of the control current/voltage and to reduce the required strength of the spring biasing the needle valve closed. The fuel injector may also include a control fuel inlet that is separate from the injection fuel inlet port.