The disclosure includes controlling a pressure ratio for a compressing system, comprising introducing a quantity of liquid into an input stream to create a multiphase input stream, compressing the multiphase input stream with a centrifugal compressor to create a discharge stream, measuring a parameter of the discharge stream, wherein the discharge parameter corresponds to a pressure ratio for the centrifugal compressor, when the parameter exceeds a first predetermined point, increasing a pressure ratio of the centrifugal compressor by increasing the quantity of liquid introduced, and when the parameter exceeds a second predetermined point, decreasing the pressure ratio by decreasing the quantity of liquid introduced.

According to an aspect, a correction factor for a fuel flow of a fuel system of an engine is determined. A nominal fuel flow is determined based on a metering valve stroke. The correction factor is applied to the nominal fuel flow to produce an estimated fuel flow to control combustion in the engine.

A mechanically driven coolant pump having a controllable delivery rate for a main delivery circuit from a first outlet and for a secondary delivery circuit from a second outlet of the coolant pump. The coolant pump comprising a hydraulic control circuit which is derived from the coolant pump and has an input-side auxiliary pump, an output-side proportional valve, and a regulating slide for limiting the flow of the main delivery circuit. A cylindrical portion of the regulating slide can be axially displaced in the pump chamber in order to radially shield the pump impeller by means of a pressure in the hydraulic control circuit counter to a restoring force. A regulating valve is connected to the hydraulic control circuit to limit the flow of the secondary delivery circuit, wherein actuations of the regulating slide and of the regulating valve are associated with pressure ranges in the hydraulic control circuit.

A power converting apparatus includes a diode bridge that converts first AC power supplied from a power supply into DC power, a main circuit capacitor (capacitors) that smooths the DC power, an inverter that converts the smoothed DC power into second AC power and supplies the second AC power to a load, a capacitor that reduces a noise component included in the first AC power, and a path switching unit (relays), and a control unit that switches a charging path for the main circuit capacitor so that current output from the power supply flows into the main circuit capacitor via the capacitors from when supply of the first AC power starts until a voltage of the main circuit capacitor reaches a predetermined voltage, and that the current output from the power supply flows into the main circuit capacitor without passing through the capacitors after the voltage of the main circuit capacitor reaches the predetermined voltage.

A flutter control system for a turbine includes a processor. The processor is configured to detect blade flutter of a turbine. The blade flutter indicates that blades of the turbine are in a deflected position different from a nominal operating position. The processor is configured to control operational parameters of the turbine that reduce or eliminate the blade flutter to improve the reliability and efficiency of the turbine.

Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.

A system for determining a side of an electrical circuit exposed to a high temperature includes a printed circuit board having at least two outer edges and first and second board stiffeners of a first material disposed along the outer edges. The system also includes a control unit and a plurality of traces formed of a material that is different than the first material and has a second Seebeck coefficient. The control unit determines whether the first edge or second edge is closer to the high temperature based on a voltage differential between a trace connecting it to the first end of the first board stiffener and a trace connecting to the first end of the second board stiffener.

Systems and methods for controlling a gas turbine engine and a propeller are described herein. A target output power for the engine and a target speed for the propeller are received. A measurements of at least one engine parameter and a measurement of at least one propeller parameter are received. At least one engine control command is generated based on the target output power, the measurement of the at least one engine parameter and at least one model of the engine. At least one propeller control command is generated based on the target speed, the measurement of the at least one propeller parameter and the at least one model of the propeller. The at least one engine control command is output for controlling an operation of the engine accordingly and the at least one propeller control command is output for controlling an operation of the propeller accordingly.

A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.