A control device includes a fuel equivalent value calculation unit for determining the flow rate of fuel supplied to a gas turbine in accordance with a target value deviation between an actual rotation speed and a target rotation speed, an upper limit deviation calculation unit for obtaining an upper limit deviation which is a deviation between a set upper limit output and an actual output, a lower limit deviation calculation unit for obtaining a lower limit deviation which is a deviation between a set lower limit output and the actual output, and a parameter-changing unit for changing any one parameter among the target rotation speed, the actual rotation speed, and the target value deviation so that the target value deviation decreases when the actual rotation speed decreases and the upper limit deviation is small, and so that the target value deviation increases when the actual rotation speed increases and the lower limit deviation is small.

A method for operating an electronically commutated fuel pump with an upstream fuel pump electronics unit of a motor vehicle, wherein the fuel pump is operated at a predefined speed, the method includes detecting a speed irregularity of the electronically commutated fuel pump, the speed irregularity being determined by examining the synchronicity between rotary field and rotor of the fuel pump, and switching over the speed of the electronically commutated fuel pump to a higher speed value than the predefined speed until a stable operation of the fuel pump without loss of synchronicity between rotary field and rotor of the fuel pump is achieved, the switchover of the fuel pump to the higher speed is performed by a predefined speed jump or is performed at predefined speed steps, the speed being increased until stable operation of the fuel pump is achieved.

A motor controller for an electric motor is provided, including a drive circuit and a processor. The drive circuit regulates power supplied to a stator of the electric motor to turn a rotor and blower to generate an airflow. The processor receives an air density, an airflow rate demand, and at least one of a measured torque and a measured speed of the electric motor. The processor computes one of a torque set point and a speed set point for the electric motor using an airflow algorithm and based on the air density, the airflow rate demand, and the at least one of the measured torque and the measured speed. The processor controls the drive circuit based on the one of the torque set point and the speed set point to supply electrical power to the electric motor and to operate the blower to generate the airflow.

A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.

An aircraft and method of flying an aircraft are disclosed. The aircraft includes a cross-feed unit that receives a flight command for the aircraft and determines an amount of fuel for a motor of the aircraft in order to reduce a droop in the aircraft when executing the flight command at the aircraft. A fuel injector or fuel supplier provides the determined amount of fuel to the motor when the flight command is executed at the aircraft.

An output ring gear for use in an integrated drive generator has a gear body extending between a first end and a second end and having a disc extending radially outwardly. A boss extends from the disc toward the second end. There are outer gear teeth outwardly of an outer diameter of the disc. There are inner gear teeth inwardly of an inner surface of the disc. The outer and inner gear teeth have a unique gear tooth profile with roll angles A, B, C, and D. An integrated drive generator and a method are also disclosed.

An assembly including a first turbocharger, the first turbocharger including a first turbine and a first compressor, the first turbine arranged in a turbine flowpath to be driven in rotation by an exhaust gas flowing at a variable flow rate through the turbine flowpath. The first compressor arranged in a compressor flowpath to be driven by the first turbine to urge an intake gas to flow through the compressor flowpath. The first turbine and first compressor being supported for rotation in bearings supplied via an oil flowpath at an oil pressure. The assembly further including a seal arranged between the oil flowpath and the compressor flowpath to resist leakage of the oil into the compressor flowpath and a flow control means configured to control a rotational speed of the first turbine and first compressor by controlling the flow of exhaust gas in the turbine flowpath.

The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: one operating mode, called speed mode, in which the pitch () of the propeller is controlled as a function of the desired propeller speed, while the fuel flow is controlled as a function of the desired torque; the other operating mode, called mode, in which the fuel flow is controlled as a function of the desired propeller speed, the pitch () of the propeller being set to a limit angle (min) that limits the pitch of the propeller in the two operating modes, the pitch angle (min(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.

A method of controlling a fuel supply device of at least one aircraft propulsion system. The method includes a step of determining the state of the fuel flowrate control system following a change of state that has moved it away from an initial state, a step of modifying the pressure of the fuel as a function of the state of the fuel flowrate control system that has been determined, and a step of changing the state of the fuel flowrate control system to return it to or toward the initial state.

A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.