A compressor system includes a compressor that includes an impeller configured to compress a working fluid by rotation. The compressor includes a housing in which an inflow flow path and a discharge flow path are formed, a guide vane that is provided in the inflow flow path and has an angle that is changeable, a diffuser vane that is provided in the discharge flow path and has an angle that is changeable, and a control unit configured to control angles of the guide vane and the diffuser vane. The control unit controls an angle of at least one of the guide vane and the diffuser vane based on a requested PQ characteristic value and a rotational speed of the impeller.

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a plurality of blades disposed about the air inlet and each pivotable about one end of the blade, the blades extending through a slot in the air inlet wall when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a plurality of first blades disposed about the air inlet and each pivotable about one end of the blade, and a plurality of second blades axially adjacent to the first blades and disposed about the air inlet and each pivotable about one end of the blade, the first and second blades extending through a slot in the air inlet wall when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes. At least one sensor is configured to measure a condition of the gas turbine engine. A controller is configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor.

A turbomachine includes a casing having an inlet end opposite an outlet end along a longitudinal axis of the casing; a shaft assembly provided within the casing, the shaft assembly extending from the inlet end to the outlet end; a plurality of rotating impellers extending radially outward from the shaft assembly; and a communication channel defined between two adjacent impellers to permit a backflow of fluid from a diffuser channel of a downstream impeller to a return channel of an adjacent upstream impeller.

An example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

A variable vane assembly for a gas turbine engine having an actuating system including a rotatable face gear and a respective pinion engaged to and extending transversely from the end of each of the moveable vanes. The teeth of each pinion define land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith. A smallest axial distance between the adjacent land surfaces of the meshed pinion and face gear teeth define a backlash of the actuating system. At least one shim has a thickness adjusting an axial distance between the pinion and the face gear to set the backlash to a predetermined value. An engine with a compressor with a variable vane assembly and a method of adjusting angular variance in an actuating system for variable vanes are also discussed.

An assembly can include a compressor housing, an adjustable wall disposed within the compressor housing that defines an air inlet to an inducer portion of a compressor wheel, and an adjustment mechanism to adjust the wall and thereby adjust at least a diameter of the air inlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

A product and method are disclosed for use with an engine including an intake passage providing combustion air to the engine. An exhaust passage may channel expelled combustion gases from the engine. A first compressor may be disposed in the intake passage, and a turbine may be disposed in the exhaust passage and may be coupled to the first compressor. The turbine may be arranged to rotate as a result of a flow of exhaust gases through the exhaust passage to drive the first compressor. A flow control device may be disposed in the intake passage upstream from the first compressor. An alternate passage may be provided having a first end opening to the intake passage upstream from the flow control device and having a second end opening to the intake passage downstream from the flow control device. A second compressor may be disposed in the alternate passage, with a drive unit adapted to drive the second compressor. The flow control device may be adapted to be closed to substantially prevent flow through the intake passage and to be open to impart swirl to a gas stream in the intake passage.

Methods and systems for controlling a chiller system to achieve control stability while maintaining optimum efficiency. Particularly, methods and systems for controlling a centrifugal compressor speed and an inlet guide vane position that establishes three distinct regions in the control path: (i) during initial unloading from full load, the inlet guide vane position is kept at a fully open position while the centrifugal compressor speed is changed to achieve the desired cooling capacity; (ii) between an inflection point and a transition point, keeping the centrifugal compressor speed constant while the inlet guide vane position is changed to achieve the desired cooling capacity; and (iii) between the transition point and zero cooling capacity, changing both the inlet guide vane position and the centrifugal compressor speed to achieve the desired cooling capacity.