The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, the system includes a pump, a hydromechanical group, a drive device positioned to drive the pump, and a branch comprising actuators for controlling variable geometry. In some embodiments, the system regulates a fuel flow rate based at least in part on a flow rate set point value. In some embodiments, the system may include a flow rate sensor. A flow rate loop may be arranged to determine a pressure set point value at the outlet of the pump according to the flow rate set point value and a measurement supplied by the flow rate sensor. In some embodiments, a pressure sensor may be positioned in the fuel circuit at the outlet of the pump. In further embodiments, a pressure loop may control the speed of the drive device based at least on a difference between a pressure measurement supplied by the pressure sensor and the pressure set point value.

An aircraft engine, has: an inlet extending circumferentially around a central axis; an annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet; a flow restrictor extending across the annular inlet duct and being movable within the annular inlet duct; an actuator engaged to the flow restrictor and operable to move the flow restrictor; and a controller operatively connected to at least one sensor and the actuator, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and containing instructions for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor; and powering the actuator to move the flow restrictor with the actuator from a first position to a second position offset from the first position as a function of the pressure difference.

A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.

A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.

A flow metering system includes a pump configured to urge a fluid flow from a fluid source, and a recirculation line located at the pump. A pressure regulating valve is located along the recirculating line. One or more fluid delivery lines extend downstream of the pump to deliver the fluid flow to one or more fluid consumers. A flow control valve is located along each fluid delivery line of the one or more fluid delivery lines. A system controller is operably connected to the pressure regulating valve and the one or more flow control valves. The system controller is configured to maintain a selected delta pressure and a selected flow rate of the fluid flow by operation of the pressure regulating valve and the one or more flow control valves.

A fuel pump system can include a motor and a pump connected to the motor. The pump can be configured to receive an inlet flow from an inlet line, to pressurize the inlet flow, and to output a pressurized flow to an output line for an engine. The system can include a bypass line disposed between the outlet line and the inlet line, and a bypass valve disposed on the bypass line and configured to allow pressurized flow to flow to the inlet line in an open state, and to prevent pressurized flow from flowing to the inlet line in a closed state. The bypass valve can be configured to allow pressurized flow to flow to the inlet line to circulate flow and to maintain a constant pressure on the output line.

A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

There are described methods, systems, and assemblies for monitoring a bleed valve of a gas turbine engine. The method comprises determining a rate of change of a gas generator speed of the gas turbine engine; determining a rate of change of a parameter indicative of engine power of the gas turbine engine; comparing at least one ratio based on the rate of change of the gas generator speed and the rate of change of the parameter indicative of engine power to at least one range of values; detecting a modulation delay of the bleed valve when the at least one ratio is within the at least one range of values; and transmitting a signal indicative of the bleed valve malfunction in response to detecting the modulation delay.

A metering valve spool controls a volume of fuel passing through a metering valve. The spool has a forward face. A line from a pump has a connection into a chamber. The face of the metering valve spool may contact a seal to block flow into the chamber. The metering valve is connected to a pressure regulating valve. The pressure regulating valve is to be connected to a combustor. A control selectively moves the metering valve spool to control a volume of fuel delivered from the chamber to the pressure regulating valve. The control is also programmed to move the metering valve spool to a position where a forward face of the metering valve spool seals on the seal to block flow from the pump from reaching the pressure regulating valve, and also from reaching the tap. A gas turbine engine is also disclosed.

A seal gas supply control method according to the present invention comprises a step for detecting a pressure difference between an internal pressure of a rotary machine and a supply pressure of a seal gas with respect to a dry gas seal portion, a step for adjusting an opening degree of a seal gas supply valve on the basis of the detected pressure difference between the internal pressure and the supply pressure, and a step for detecting a vent pressure for discharging the seal gas evacuated from the dry gas seal portion to the outside. The seal gas supply control method fully opens the seal gas supply valve when the detected vent pressure satisfies a predetermined condition.