The present disclosure relates to systems and methods that are useful in control of one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants, methods of starting power production plants, and methods of generating power with a power production plant wherein one or more control paths are utilized for automated control of at least one action. The present disclosure more particularly relates to power production plants, control systems for power production plants, and methods for startup of a power production plant.

The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

A combustion staging system includes a splitting unit which receives a metered fuel flow and controllably splits the received fuel flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel from the splitting unit to the pilot and mains stages. The splitting unit selects and deselects pilot-only operation. Both pilot and mains manifolds are selectable for pilot and mains operation. A cooling flow recirculation line has a delivery section arranged to provide a cooling flow of fuel to the mains manifold when it is deselected during pilot-only operation. Cooling flow enters the delivery section from a high pressure fuel zone of the engine and exits the return section to a low pressure fuel zone of the engine. A controller adjusts the splitting unit during pilot-only operation to partially select the mains manifold thereby increasing the pressure in the mains manifold to meet a target fuel pressure therein.

An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner.

An aircraft including lean-burn gas turbine engines operating in pilot-plus-mains mode with a given initial fuel flow W.sub.0, a method of controlling the optical depth of contrails produced by a first group of engines includes the steps of (i) reducing fuel flow to each engine in the first group to change the operation of each engine from pilot-plus-mains mode to pilot-only mode, and (ii) adjusting fuel flow to one or more engines in a second group of engines such that the total fuel flow to engines of the second group is increased, all engines of the second group remaining in pilot-plus-mains mode, and wherein the set of lean-burn engines consists of the first and second groups. Depending on atmospheric conditions, the average optical depth of contrails produced by the engines may be enhanced or reduced compared to when all engines operate in pilot-plus-mains mode with a fuel flow W.sub.0.

A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.

A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.

A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path configured to supply fuel to a first fuel injection hole defined in the nozzle main body; a second fuel flow path configured to supply fuel to a second fuel injection hole defined in the nozzle main body on a radial outer side of the first fuel injection hole; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel in the first fuel flow path; a temperature sensor-configured to detect a temperature on a downstream side of the swirl vane; and a control device configured to control the first regulating valve so that the flow rate of the fuel in the first fuel flow path is lowered when the temperature detected by the temperature sensor satisfies a predetermined condition.

A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path configured to supply fuel to a first fuel injection hole defined in the nozzle main body; a second fuel flow path configured to supply fuel to a second fuel injection hole defined in the nozzle main body on a radial outer side of the first fuel injection hole; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel in the first fuel flow path; a temperature sensor-configured to detect a temperature on a downstream side of the swirl vane; and a control device configured to control the first regulating valve so that the flow rate of the fuel in the first fuel flow path is lowered when the temperature detected by the temperature sensor satisfies a predetermined condition.