A vacuum pump that allows for timely inspection and replacement of a temperature adjustment means, prevents unexpected stopping, and limits the maintenance cost, and a controller that controls the vacuum pump are proposed. The present disclosure relates to a vacuum pump for exhausting gas from an apparatus, such as manufacturing equipment, subjected to exhaustion. The vacuum pump includes: a temperature adjustment means for causing a predetermined area of the vacuum pump to have a predetermined temperature; an output control means configured to operate the temperature adjustment means; and an information output means configured to output information regarding ON/OFF of the temperature adjustment means obtained from the output control means.

A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.

The present application provides a hazardous gas detection system to determine hazardous gas concentrations and/or temperatures within a flow of exhaust air in an exhaust duct of a gas turbine compartment. The hazardous gas detection system may include one or more sensors positioned within or in communication with the exhaust duct and a static mixer positioned upstream of the one or more sensors to promote mixing of the flow of exhaust air.

A fuel flow measuring system includes an ultrasonic fuel flow sensor. The fuel flow sensor includes a first transducer and a second transducer. The first transducer is excited at multiple different excitation frequencies and a voltage, an electric current, and a phase difference between the voltage and the electric current is sensed at the first transducer during excitation. Data points are generated based on the sensed readings and a model is fit to the data points to determine a complex impedance spectrum. The complex impedance spectrum indicates a range of excitation frequencies within a range of a peak resonance frequency of the first transducer. One or more characteristics of excitation signals directed to the second transducer are set based on the determined complex impedance spectrum. In this manner, the signal to noise ratio of ultrasonic signals emitted by the second transducer and received by the first transducer can be maximized.

The invention relates to a method for controlling a pitch angle of the vanes or blades of a propellant body of a turbine engine, comprising generating a pitch command (i.sub.final) according to a rotational speed of the propeller (XN.sub.mes) and a speed setpoint (XN.sub.cons), the method comprises a nominal regulating chain (13), wherein the pitch command is further generated according to a value of a pitch angle (βmes) of the vanes or blades of the propellant body, and an off-nominal regulating chain (16), wherein the pitch command is generated independently of a value of a pitch angle of the vanes or blades of the propellant body.

A motor includes: a first portion that includes a plurality of permanent magnets; and a second portion that includes a plurality of coils, wherein the first portion or the second portion is configured to be rotatable around a rotation axis, wherein the plurality of permanent magnets are circumferentially arranged about the rotation axis, and wherein the plurality of coils are arranged so as to face the plurality of permanent magnets in a direction along the rotation axis, and the motor further includes: a control unit that controls a rotational speed and an attitude of the rotating first portion or the rotating second portion by controlling currents that are applied to the plurality of coils.

A system of a machine includes a network of a plurality of nodes distributed throughout the machine, a controller, and a power extraction system within at least one of the nodes. Each of the nodes is operable to communicate through one or more radio frequencies. The controller is configured to communicate with the network of nodes by transmitting the one or more radio frequencies through one or more waveguides. The power extraction system is configured to extract power from the one or more radio frequencies as a first power source, extract power from a second power source, and provide power to one or more components of the system based on power extracted from either or both of the first power source and the second power source.

An aircraft power plant comprising: a high-pressure spool including a high-pressure compressor, a high-pressure turbine, and a high-pressure shaft drivingly engaging the high-pressure turbine to the high-pressure compressor; a low-pressure spool including a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft drivingly engaging the low-pressure turbine to the low-pressure compressor; an electrical machine operable as a generator; and a transmission having a first input drivingly engaged by the high-pressure shaft, a second input drivingly engaged by the low-pressure shaft, and an output drivingly engaging the electrical machine, the transmission having a coupling system selectively interconnecting the output with one of: the first input, with the second input disconnected from the output; the second input, with the first input disconnected from the output; and both of the first input and the second input.

A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.