Abstract: The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, and wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold.

Abstract: A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Abstract: A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Abstract: A method is provided for performing a transfer from gas fuel operation to liquid fuel operation in a gas turbine with a dual fuel system. The method includes initiating a predetermined uncontrolled liquid fuel prefill flow rate through the liquid fuel system, sensing an onset of the uncontrolled liquid fuel flow to the combustor nozzles, and initiating transfer from gas fuel operation to liquid fuel operation when the flow of uncontrolled liquid fuel at the combustor nozzles is sensed. The onset of uncontrolled liquid fuel flow to the combustor nozzles is determined by monitoring changes of Fuel Normalized Power (FNP), a parameter sensitive to uncontrolled liquid fuel flow, and determining when FNP exceeds a threshold algorithm value.

Abstract: The present application provides a method of operating a dual gas fuel delivery system comprising selecting a manifold and fuel flow split; setting the stroke of a high-energy gas control valve based on the fuel split; measuring the primary manifold nozzle pressure ratio across a primary manifold nozzle outlet; comparing the primary manifold nozzle pressure ratio against a primary manifold specification limit; adjusting the stroke of a primary low energy gas control valve to maintain the pressure ratio across the primary manifold nozzle outlet within the primary manifold specification limit; measuring the secondary manifold nozzle pressure ratio across a secondary manifold nozzle outlet; comparing the secondary manifold nozzle pressure ratio against a secondary manifold specification limit; and adjusting the stroke of a secondary low energy gas control valve to maintain the pressure ratio across the secondary manifold nozzle outlet within the secondary manifold specification limit.

Abstract: A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Abstract: A method for controlling the rate of transfer between operation with gas and liquid fuel types to minimize the time in undesirable operational mode, thereby preventing excessive wear and damage to gas turbine hardware. The method includes completing a fuel prefill for the oncoming fuel type through the fuel system and determining if a total fuel demand for the oncoming fuel type is greater than a predetermined flow rate for the oncoming fuel type. The method also includes selecting a fuel transfer rate and transferring from the offgoing fuel type to the oncoming fuel type at the selected fuel transfer rate. Further, the method includes determining if the offgoing fuel flowrate has decreased below a predetermined flow rate for the offgoing fuel type, selecting a final fuel transfer rate and completing the transfer from offgoing fuel type to oncoming fuel type at a selected final fuel transfer rate.

Abstract: The present application provides a method of operating a dual gas fuel delivery system comprising selecting a manifold and fuel flow split; setting the stroke of a high-energy gas control valve based on the fuel split; measuring the primary manifold nozzle pressure ratio across a primary manifold nozzle outlet; comparing the primary manifold nozzle pressure ratio against a primary manifold specification limit; adjusting the stroke of a primary low energy gas control valve to maintain the pressure ratio across the primary manifold nozzle outlet within the primary manifold specification limit; measuring the secondary manifold nozzle pressure ratio across a secondary manifold nozzle outlet; comparing the secondary manifold nozzle pressure ratio against a secondary manifold specification limit; and adjusting the stroke of a secondary low energy gas control valve to maintain the pressure ratio across the secondary manifold nozzle outlet within the secondary manifold specification limit.

Abstract: The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, and wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold.

Abstract: A method for controlling the rate of transfer between operation with gas and liquid fuel types to minimize the time in undesirable operational mode, thereby preventing excessive wear and damage to gas turbine hardware. The method includes completing a fuel prefill for the oncoming fuel type through the fuel system and determining if a total fuel demand for the oncoming fuel type is greater than a predetermined flow rate for the oncoming fuel type. The method also includes selecting a fuel transfer rate and transfering from the offgoing fuel type to the oncoming fuel type at the selected fuel transfer rate. Further, the method includes determining if the offgoing fuel flowrate has decreased below a predetermined flow rate for the offgoing fuel type, selecting a final fuel transfer rate and completing the transfer from offgoing fuel type to oncoming fuel type at a selected final fuel transfer rate.

Abstract: A method is provided for performing a transfer from gas fuel operation to liquid fuel operation in a gas turbine with a dual fuel system. The method includes initiating a predetermined uncontrolled liquid fuel prefill flow rate through the liquid fuel system, sensing an onset of the uncontrolled liquid fuel flow to the combustor nozzles, and initiating transfer from gas fuel operation to liquid fuel operation when the flow of uncontrolled liquid fuel at the combustor nozzles is sensed. The onset of uncontrolled liquid fuel flow to the combustor nozzles is determined by monitoring changes of Fuel Normalized Power (FNP), a parameter sensitive to uncontrolled liquid fuel flow, and determining when FNP exceeds a threshold algorithm value.

Abstract: A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Abstract: In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.

Abstract: A computer implemented process is provided for assessing and characterizing the degree of success or failure of an operational event of a machine system such as a fluid compressor machine or turbine machine or the like on a continuous numerical scale. The computer implemented process develops and tracks machine unit signatures, machine site signatures and machine fleet signatures to evaluate various operational events and provide fault detection. At least some sensor data acquired from the machine system during an operational event is transformed to correct or at least reduce variabilities in the data caused by ambient conditions and fuel quality. The transformed data is then analyzed using statistical methods to determine how closely the operational event conforms to an expected normal behavior and the information is used to develop a single comprehensive quality assessment of the event.

Abstract: An apparatus and method of applying active, closed loop control to reduce combustion driven pressure oscillation in a single or multi-chamber combustion system in an industrial gas turbine, to increase operability and life of the parts, and in such a way as to require minimal input power. The invention combines the passive control of a two stage nozzle with active control thereby to reduce the requirements on the control device. This allows selection of a control device which will have an adequate life in an industrial environment and yet require minimal input power.

Abstract: A purge system is disclosed for flushing liquid fuel and water from the combustion section of a gas turbine system as well as for providing continuous cooling of the nozzles. The gas turbine may operate on liquid fuel or gaseous fuel. When the turbine is switched to burn gaseous fuel, the liquid fuel remaining in the liquid fuel system is flushed by a liquid fuel purge system. Similarly, water in the water injection system is purged from nozzles in the combustion system by a water purge system. The purge system operates in conjunction with an air atomization system, but does not rely on an atomizing air compressor to boost the pressure of the purge air. Instead, the purge system utilizes pressurized air from the gas turbine compressor and directs the purge air to manifolds which distribute air to the atomizing air passages, liquid fuel nozzles, and water injection nozzles via purge valves and soft purge valves.

Abstract: A method for detecting flashback events in gas turbine is disclosed. The method employs periodic reference point checks to determine whether or not flashback damage has occurred. The method relies on the repeatability of exhaust profile and NOx as functions of precise turbine conditions. In combination with experience-based limits, changes in these values are used to determine if a flashback has occurred, even days later.

Abstract: A fuel trimming unit has been adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine. The fuel trim unit matches the combustion air flow into each combustion chamber. This adjusts the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each combustion chamber. Because of the fuel trim unit, a uniform fuel-air mixture is provided to each combustion chamber in a gas turbine. The fuel trim unit is adjusted using sensor inputs of the fuel flow rate to each combustion chamber, the dynamic pressure in each combustion chamber, and the turbine exhaust temperature.

Abstract: A fuel trimming unit has been adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine. The fuel trim unit matches the combustion air flow into each combustion chamber. This adjusts the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each combustion chamber. Because of the fuel trim unit, a uniform fuel-air mixture is provided to each combustion chamber in a gas turbine. The fuel trim unit is adjusted using sensor inputs of the fuel flow rate to each combustion chamber, the dynamic pressure in each combustion chamber, and the turbine exhaust temperature.

Abstract: A fuel trimming unit has been adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine. The fuel trim unit matches the combustion air flow into each combustion chamber. This adjusts the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each combustion chamber. Because of the fuel trim unit, a uniform fuel-air mixture is provided to each combustion chamber in a gas turbine. The fuel trim unit is adjusted using sensor inputs of the fuel flow rate to each combustion chamber, the dynamic pressure in each combustion chamber, and the turbine exhaust temperature.