A fuel conditioning and control system provides dynamic control and steady state operations of a gas turbine provided fueled by supercritical liquefied petroleum gas (LPG). The fuel conditioning and control system comprises a storage for LPG fuel; a fuel delivery sub-system connecting the storage to turbomachinery; and a control system. The gas turbine includes a gas turbine core control that provides at least one operational data of the gas turbine to the control system. The fuel delivery sub-system includes at least one sensor for sensing at least one property of the LPG fuel in the fuel delivery sub-system, where the at least one sensor providing data on the at least one property of the LPG fuel to the control system. The control system analyzes the data on the at least one property of the LPG fuel and at least one operational data of the gas turbine for dynamic control of LPG fuel to the gas turbine under dynamic and steady state conditions.

A liquid fuel rocket engine according to one example includes a combustor, a liquid fuel repository connected to the combustor via a fuel line and a first valve, an oxidizer repository connected to the combustor via an oxidizer line and a second valve, a valve controller configured to output a valve control current to the first valve, the valve controller storing instructions for determining at least one actual minimum impulse bit of a valve based on a current profile and a voltage profile of a single operation of the first valve, and to adjust valve controls to account for the at least one actual minimum impulse bit.

An electric power dissipater assembly for an electrically-actuated turbocharger that includes: a power switch configured to be electrically connected to an electric power output of an electrically-actuated turbocharger; at least one resistor that is electrically connected to the power switch such that, when the power switch is in a closed position and connected to the electric power output, the at least one resistor is electrically coupled to the electric power output so that electric power provided by the electrical power output is received at and dissipated by the at least one resistor; a controller that controls whether the power switch is in the closed position or an open position; and a substrate that is physically coupled to the at least one resistor and that includes a coolant path that is used to cool the at least one resistor when coolant is received within the coolant path.

To control an engine shutdown in an aircraft, a control system includes a fuel supply shut-off member, a control member with a set of switches, a first switch on an electrical power supply link of the fuel supply shut-off member and second switches connected to avionics of the aircraft, the set of switches switching position on an engine shutdown command. An engine shutdown confirmation unit includes a third switch on the electrical power supply link, the third switch in open position by default. The engine shutdown confirmation unit includes electronic circuitry configured to switch the third switch over to closed position when a predefined quantity Q of switches of the control member switches position within a sliding window of predefined duration and, otherwise, keeps the third switch in open position. Thus, it is ensured that the engine shutdown is intentional.

A method for controlling the direction of rotation of a fluid machine having an oriented-blade impeller, comprising the following steps:

starting (100) a synchronous electric motor which operates said fluid machine until the synchronous state is reached;

driving (200) said synchronous electric motor at steady state by applying a phase cutting;

applying (300) a phase cutting corresponding to a reference power, wherein said reference power is comprised between a first power required to keep the propeller rotating in a right direction and a second power required to keep the propeller rotating in a wrong direction, which is opposed to the right direction.

An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.

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 that smooths the DC power, one or more capacitors that reduces a noise component included in the first AC power, and a path switch. The path switch switches a charging path for the main circuit capacitor so that current output from the AC power supply flows into the main circuit capacitor via the capacitor(s) 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 AC power supply flows into the main circuit capacitor without bypassing the capacitor(s) after the voltage of the main circuit capacitor reaches the predetermined voltage.

A fuel conditioning and control system provides dynamic control and steady state operations of a gas turbine provided fueled by supercritical liquefied petroleum gas (LPG). The fuel conditioning and control system comprises a storage for LPG fuel; a fuel delivery sub-system connecting the storage to turbomachinery; and a control system. The gas turbine includes a gas turbine core control that provides at least one operational data of the gas turbine to the control system. The fuel delivery sub-system includes at least one sensor for sensing at least one property of the LPG fuel in the fuel delivery sub-system, where the at least one sensor providing data on the at least one property of the LPG fuel to the control system. The control system analyzes the data on the at least one property of the LPG fuel and at least one operational data of the gas turbine for dynamic control of LPG fuel to the gas turbine under dynamic and steady state conditions.