Provided is a vacuum pump that can realize energy conservation when performing abatement of exhaust gas.

A vacuum pump that sucks in and exhausts exhaust gas includes a motor serving as a drive source, and a first controller that controls driving of the motor. The first controller monitors a state of the motor, and in a case in which the state of the motor is a specific state excluding when starting up and when stopped, outputs a specific signal (process signal) to an external entity.

Methods, systems, and assemblies for operating an aircraft having a turboprop engine are described. The method comprises obtaining a measured torque of the turboprop engine from a mechanical torque piston measurement system and displaying the measured torque in a cockpit of the aircraft. During operation of the turboprop engine, a torque measurement saturation condition of the torque piston measurement system is monitored to detect when the torque piston measurement system is outside of an operating range. A synthesized torque of the turboprop engine is determined based on one or more actual engine operating parameters of the turboprop engine. In response to detecting that the torque piston measurement system is outside of the operating range, the synthesized torque is displayed in the cockpit of the aircraft.

The aircraft can have a first engine secured to a first wing on a first side of a fuselage, and a second engine secured to a second wing on a second side of the fuselage, the second wing having a proximal end secured to the fuselage, and a distal end extending away from the fuselage. While operating the first engine, compressed gas can be conveyed from the first engine to a thrust generating device located at the distal end of the second wing.

A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

An operation control device for a single shaft gas turbine selects an operation mode based on a load state of a power generator, and controls the turbine based on the operation mode. In a first operation mode, a rotational speed of the turbine is maintained within a first rotational speed range, and in a second operation mode, the rotational speed is maintained within a second rotational speed range set on a lower rotational speed side than the first rotational speed range. The second rotational speed range is set on the lower rotational speed side than the first rotational speed range with a first non-selection rotational speed range set therebetween.

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

A method and system for detecting a functional failure in a power gearbox, includes engine a) measuring operational data in a gas turbine engine of operational parameters dependent on power generation and power consumption of the engine or the gearbox, b) obtaining analyzed operational data including time data, angular data of rotation, frequency data and/or phase data, c) using the analyzed operational data in a comparison with stored baseline operational data to determine deviation data, d) determining time dependent trend data from the deviation data or determining a first state measured dependent on the power generation, power consumption or power regulation of the engine and measuring a second state dependent on vibrational data of the engine, e) generating a signal and/or a protocol for controlling the gearbox, and/or the engine based on the time dependent trend data, if a threshold is exceeded or based on the first or second states.

The invention relates to a method for determining a fluid conveying parameter, a fluid conveying device, particularly for determining a volumetric flow, comprising the steps of Determining excitation information for mechanical excitation of at least one fluid conveying element of the fluid conveying device in at least one spatial direction by at least one first sensor means, Providing operating information, comprising at least a value of an operating variable of the fluid conveying device by means of a providing means, Analyzing the information provided and determined, Determining a fluid conveying parameter, particularly a volumetric flow, of the fluid conveying device based on the analyzed information.

Systems and methods for adjusting a variable geometry mechanism of an engine are described herein. An engine control request indicative of a desired output power for the engine is monitored. A rate of change of the engine control request is determined. The rate of change is compared to a threshold. Responsive to determining that the rate of change is beyond the threshold, a transient bias map is applied to a steady-state schedule to generate a variable geometry mechanism request indicative of a target position for the variable geometry mechanism. The variable geometry mechanism is adjusted toward the target position according to the variable geometry mechanism request.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.