A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.

Embodiments of a compressor stage, in particular for a turbocharging system and/or a turbocompound, and a process for operating a compressor stage are provided herein. The compressor stage comprises an impeller, and a vaned diffuser arranged downstream of the impeller. The vaned diffuser is in fluid connection with an outlet of the impeller and comprises an injection device configured to inject a secondary fluid into the vaned diffuser. The injection device comprises a displaceable port at least partially arranged between an adjacent pair of vanes of the diffuser.

A control device includes: a variation command unit that changes a command value, which is a command value sent to a system including a compressor, affecting an operating state of the compressor; a proportional coefficient calculation unit that calculates a proportional coefficient of a variation in a parameter, which indicates a state of the compressor or an electric motor that drives the compressor when the system is operated based on the command value, with respect to the command value; and a control unit that performs control for avoiding or suppressing surging in the compressor, based on a value of the proportional coefficient.

The method can include determining a mass flow rate W of working fluid circulating through the compressor stage, determining a control parameter value associated to the geometrical configuration of the variable geometry element based on the determined value of mass flow rate W; and changing the geometrical configuration of the variable geometry element in accordance with the determined control parameter value.

An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

An HVAC system includes an unloading device, a centrifugal compressor, a gas foil bearing, a VFD and a controller. The controller is programmed to start the centrifugal compressor from a stopped condition by operating the unloading device to remove a load from the centrifugal compressor, accelerating the motor to a first speed above a liftoff speed of the gas foil bearing and below an operating speed of the centrifugal compressor, running the motor for a period of time, operating the unloading device to apply the load to the centrifugal compressor, and accelerating the motor to the operating speed.

Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

A rotary apparatus for inputting thermal energy into fluidic medium is provided, the apparatus comprises: a casing with at least one inlet and at least one outlet; a rotor comprising at least one row of rotor blades configured as impulse impeller blades arranged over a circumference of a rotor hub mounted onto a rotor shaft; at least one row of stationary nozzle guide vanes arranged upstream of the at least one row of the rotor blades, respectively; and at least one row of stationary diffuser vanes arranged downstream of the at least one row of the rotor blades, respectively. The apparatus is configured to impart an amount of thermal energy to a stream of fluidic medium directed along a flow path formed inside the casing between the inlet and the outlet by virtue of a series of energy transformations occurring when said stream of fluidic medium successively passes through the blade/vane rows formed by the nozzle guide vanes, the rotor blades and the diffuser vanes, respectively, wherein, in said apparatus, a space formed between an exit from the at least one row of diffuser vanes and an entrance to the at least one row of nozzle guide vanes in a direction of the flow path formed inside the casing between the inlet and the outlet is made variable to regulate the amount of thermal energy input to the stream of fluidic medium propagating through the apparatus. Related uses and a method for inputting thermal energy into a fluidic medium are further provided.

Provided is a compressor control device configured to control a flow rate of a compressor having a plurality of impellers connected to an outlet port-side flow path in parallel and a flow rate regulation unit configured to regulate a flow rate of each of the impellers, the compressor control device including a pressure detection unit configured to detect a pressure of the outlet port-side flow path, a flow rate detection unit configured to detect the flow rate of each of the impellers, and a control unit configured to output a flow rate regulation command of each of the impellers to the flow rate regulation unit and control the flow rate regulation unit based on the detection result of the pressure detection unit.

A diffuser assembly for a compressor is provided. The diffuser may include a first stationary wall and a second stationary wall coupled with one another and forming at least in part a volute configured to receive compressed process fluid from the diffuser. The second stationary wall may define a plurality of stationary wall grooves. The diffuser may also include a moveable wall defining a plurality of moveable wall grooves. The moveable wall may be disposed between the first stationary wall and the second stationary wall such that respective stationary wall grooves and moveable wall grooves form respective flow passages configured to receive the flow of process fluid exiting an impeller of the compressor. The diffuser assembly may also include an actuator assembly configured to displace the moveable wall to alter a cross-sectional area of each of the flow passages based on a flow rate of the process fluid.