A combustion staging system includes a splitting unit receiving a metered fuel flow and controllably splitting the received flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel. A cooling flow recirculation line provides a cooling flow to the mains manifold during pilot-only operation, and a return section to collect mains manifold cooling flow. The cooling flow enters a delivery section and exits the return section. A fuel recirculating control valve on the delivery section has an open position so that the cooling flow enters the delivery section during pilot-only operation; a shut off position prevents the cooling flow entering the delivery section through the cooling flow orifice during pilot and mains operation. A supplementary valve bleeds or feeds cooling flow. The mains manifold cooling flow pressure is determined by the cooling flow and pressure raising orifices flow numbers, and a control setting of the supplementary valve.

An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.

A delay time calculation method is a method for calculating a delay time in a facility including a fuel line for introducing a fuel gas to a supply target device, and a calorimeter for measuring a calorie of the fuel gas obtained from a measurement point of the fuel line, the delay time indicating a time difference between when the calorie of the fuel gas is measured by the calorimeter and when the fuel gas reaches the supply target device, the fuel line including a plurality of segments obtained by dividing the fuel line between the measurement point and the supply target device, the delay time calculation method including: a step of calculating a plurality of segment movement delay times respectively indicating times required for the fuel gas to pass through the plurality of segments; a step of calculating a total movement delay time which is a time required for the fuel gas to move through the fuel line from the measurement point to the supply target device, by adding up the plurality of segment movement delay times; and a step of acquiring the delay time based on the total movement delay time. The step of calculating the plurality of segment movement delay times includes acquiring the segment movement delay time based on a correlation between the segment movement delay time acquired in advance and a fuel flow rate supplied to the supply target device, for each of the plurality of segments.

The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.

The disclosure relates to optimization of gas turbine power plant response during power system transients. In certain embodiments, systems, methods, and apparatus can control a power generating system by using the reactive components of the current and the reactive components of the voltage and the magnitude of the voltage at the generator terminals of a gas turbine generator system. In one embodiment, a system can identify a power system fault based on at least three conditions occurring for a specified duration and at substantially the same time: (1) an increase in the reactive current, (2) a decrease in the magnitude of the voltage, and (3) an increase in the reactive power. In one embodiment, a power system can further detect a remote breaker open (RBO) condition, and distinguish a RBO condition from a power system fault condition.

Systems and methods for improved gas turbine engine performance are disclosed. The method can include receiving an error function for a wide range of fuels. The error function can provide lower heating value (LHV) corrections over the wide range of fuels. The method can include receiving gas turbine engine operation data for a first period of run time on the gas turbine from one or more sensors of the gas turbine engine. The engine operation data can include a performance data points. The method can include determining an optimum LHV based on the engine operation data for the first period of run time and the error function. The method can then include adjusting fuel consumption of the gas turbine engine based on the optimum LHV.

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

A method of operating a gas turbine engine is provided. The method includes: providing a flow of a primary fuel to a combustor of a turbomachine, the turbomachine including a compressor, a turbine, and a spool rotatable with the compressor and the turbine; receiving data indicative of a spool parameter of the spool; and modifying a flow of a secondary fuel to the combustor in response to the received data indicative of the spool parameter of the spool.

A method of controlling a combustor of a gas turbine engine is disclosed. The method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a pilot fuel split, monitoring at least one signal of at least one condition of the gas turbine engine, generating a steady state value of the at least one signal indicative of a steady state of the gas turbine engine, detecting a change in the at least one signal from the steady-state value. When the change in the at least one signal from the steady state value exceeds a predetermined limit, the method applies the steps generating a transient split offset for the pilot fuel split from a look-up table and applying the transient split offset to the pilot fuel split while maintaining the total fuel quantity being supplied at any point in time.

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.