In accordance with at least one aspect of this disclosure, there is provided a fuel control system for gaseous fuel in an aircraft. The system includes a control module operatively connected to a metering device in a fuel flow conduit, the control module operable to control the flow of fuel through the fuel flow conduit. The control module includes an input line operable to receive a command input indicative of a requested engine state. In embodiments, the control module includes a compressibility logic and machine readable instructions. The machine readable instruction can be configured to cause the control module to control the metering device to achieve the requested engine state based on a compressibility factor input from the compressibility logic.

A 660MW supercritical unit bypass control method after a load rejection is provided. Steam channels after the load rejection are switched without an interference, and ache steam pressure is controllable. The 660MW supercritical unit bypass control method includes Pipeline 1, Pipeline 2, Pipeline 3, and Pipeline 4; a bottom of Pipeline 3, a bottom of the Pipeline 2, and a head of the Pipeline 4 are connected by a temperature and pressure reducer; a bottom of the Pipeline 1 is connected to a head of Pipeline 2; a branch pipe is arranged between the Pipeline 1 and the Pipeline 2, and a steam turbine is arranged in the branch pipe. A high-pressure bypass control system automatically adapts to the load rejection or FCB under any loading situation, avoids drastic changes of unit parameters from loading fluctuations, meets requirements of the load rejection and the FCB.

A system for controlling a turbine is disclosed. The system includes a turbine control fuel governor that has a plurality of VCPIDs operating in parallel with one another. Each VCPID is associated with a respective turbine parameter and one or more external parameters. Each VCPID incorporates feedback from the parallel operating VCPIDs to feed an integral term of a current VCPID in the following manner: a previous derivative gain and a previous proportional gain are summed and subtracted from a selected output for the turbine to yield a result, and the result is input to an integral gain portion of the current VCPID.

A system for controlling a turbine is disclosed. The system includes a turbine control fuel governor that has a plurality of VCPIDs operating in parallel with one another. Each VCPID is associated with a respective turbine parameter and one or more external parameters. Each VCPID incorporates feedback from the parallel operating VCPIDs to feed an integral term of a current VCPID in the following manner: a previous derivative gain and a previous proportional gain are summed and subtracted from a selected output for the turbine to yield a result, and the result is input to an integral gain portion of the current VCPID.

A 660MW supercritical unit bypass control method after a load rejection is provided. Steam channels after the load rejection are switched without an interference, and ache steam pressure is controllable. The 660MW supercritical unit bypass control method includes Pipeline 1, Pipeline 2, Pipeline 3, and Pipeline 4; a bottom of Pipeline 3, a bottom of the Pipeline 2, and a head of the Pipeline 4 are connected by a temperature and pressure reducer; a bottom of the Pipeline 1 is connected to a head of Pipeline 2; a branch pipe is arranged between the Pipeline 1 and the Pipeline 2, and a steam turbine is arranged in the branch pipe. A high-pressure bypass control system automatically adapts to the load rejection or FCB under any loading situation, avoids drastic changes of unit parameters from loading fluctuations, meets requirements of the load rejection and the FCB.

A control device for a gas turbine include: a target value calculation part configured to calculate a control target value being a target value of an output of the gas turbine; and a command value calculation part configured to calculate a fuel command value on the basis of a deviation between the control target value and an actual output value of the gas turbine. The target value calculation part is configured to: set the control target value to a value which is greater than an output demand value of the gas turbine immediately before a difference between the output demand value and the actual output value becomes not greater than a threshold; and subtract the control target value from the value after the difference becomes not greater than the threshold.

A fuel supply control device controls a fuel supply pump based on a front-rear differential pressure across a metering valve for a fuel supply amount, which is detected by a differential pressure gauge, using parallel flow passages of an orifice and a pressurizing valve as the metering valve, in which the fuel supply control device includes a first control amount generation unit generating a first control amount based on the front-rear differential pressure, a second control amount generation unit generating a second control amount based on the rotation speed of the fuel supply pump, a control amount selection unit, a subtractor, and a control calculation unit, in which the control amount selection unit selects the first control amount in a case where the rotation speed is equal to or lower than a predetermined threshold and select the second control amount in a case where the rotation speed exceeds the threshold.

A method and a device for controlling a fan speed provided and may be applied to a server. According to an example of the method, a target DTS temperature curve corresponding to a current ambient temperature of the server is determined, and then, a DTS temperature corresponding to a current load of a power consumption component in the server is determined according to the target DTS temperature curve, and a speed of a fan associated with the power consumption component is adjusted according to the DTS temperature and a current temperature of the power consumption. The power consumption of the power consumption component and the power consumption of the fan are effectively balances by dynamically controlling the fan speed under different loads and at different ambient temperatures, thereby minimizing the power consumption of the server.

Disclosed is a computer-implemented method for controlling an engine system of a vehicle comprising: determining an operating condition of the vehicle; determining one or more contextual conditions relevant to the vehicle; selecting, based upon both the determined operating condition and the determined one or more contextual conditions, a control profile for the engine system from a directory comprising a plurality of control profiles having different control characteristics; applying the selected control profile to a controller of the engine system; and controlling the engine system with the controller in accordance with the selected control profile. Also disclosed are an engine control system, a gas turbine engine, and an aircraft.

A system includes a gas turbine engine and a controller operable to determine a closing threshold with respect to an upper limit and an opening threshold with respect to a lower limit of a movement range of an effector of the gas turbine engine based on an on-board model, where the upper limit and the lower limit are defined for a target parameter of the gas turbine engine. The controller determines a projected state of the target parameter absent a correction command to the effector, applies a closing correction to the effector based on determining that the projected state of the target parameter would result in being above the closing threshold, and applies an opening correction to the effector based on determining that the projected state of the target parameter would result in being below the opening threshold.