A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

A component assembly for a gas turbine engine defining a core air flowpath is provided. The component assembly includes an outer shell comprising a first array of integral outer shell airfoils that extend inward from an outer shell periphery; and an inner shell comprising a second array of integral inner shell airfoils that extend outward from an inner shell periphery, wherein the outer shell and the inner shell are one or both of translatable and rotatable relative to one another between a first position and a second position.

A turbine and method of operating the same a turbine includes a housing having a volute, an inlet and an outlet an impeller rotatable coupled to the housing, a first shroud disposed within the housing comprising a plurality of nozzle vanes and a second shroud disposed within the housing adjacent to the first shroud so that a nozzle area is formed between the first shroud and the second shroud, said nozzle area having a variable width. The second shroud is movable relative to the first shroud to vary the width so that fluid flow from the inlet to the outlet is variable.

A control valve for controlling a gaseous volumetric flow rate, in particular a steam volumetric flow rate, having a valve housing, a valve seat, and a valve throttle element which can be moved relative to the valve seat along a movement axis. The valve housing shapes the valve seat, and the movable valve throttle element has a throttle edge region which interacts with the valve seat. The control valve has multiple volumetric flow rate swirl elements which interact with the throttle edge region and which prevent or at least reduce shear layer instabilities in a shear layer between a wall jet region of the gaseous volumetric flow rate and a core flow region of the gaseous volumetric flow rate.

A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.

A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.

A solenoid for a bleed valve includes a solenoid body with an actuation fluid passage, a bleed valve passage, and a drive fluid chamber. A main armature is disposed within the solenoid body and is movable between open and closed positions, the actuation fluid passage being in fluid communication with the control outlet in the open position, the actuation fluid passage being fluidly isolated from the bleed valve passage in the second position. A pilot armature is disposed within the solenoid body, is movable relative to the main armature, and is operably coupled to the main armature by the drive fluid chamber to move the main armature between the open and closed positions by controlling issue of a drive fluid into and out of the drive fluid chamber.

An assembly includes a first enclosed flexible pressure chamber. A first extension arm extends from a first endwall of the first enclosed flexible pressure chamber. A second enclosed flexible pressure chamber includes a second extension arm extending from a second endwall of the second enclosed flexible pressure chamber. A lever arm is disposed on a pivot. A first end of the lever arm is attached to the first extension arm and a second end of the lever arm is attached to the second extension arm. A variable restriction element is connected to the second end of the lever arm.

An exhaust turbocharger includes an air-guiding section. A spiral channel is formed downstream of a wheel chamber in the air-guiding section. Between the wheel chamber and the spiral channel, a diffuser channel is formed in the air-guiding section. Upstream of the wheel chamber, an inlet channel is formed in the air-guiding section for the inflow of fluid to be compressed. In the inlet channel, a cross-section-changing unit. The cross-section-changing unit comprises an operating element with at least two movable element parts to produce a baffle which can protrude, with the aid of an adjusting unit, into the inlet cross-section rotationally and/or in a translational manner or can be removed from the inlet cross-section. The two element parts are fixedly disposed at one element end jointly in the air-guiding section. A relative movement of the element parts can be brought about in particular in an opposing direction.

A centrifugal compressor for a turbocharger includes a passive or semi-passive inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position solely by aerodynamic forces on the mechanism. The inlet-adjustment mechanism includes a plurality of flexible vanes collectively forming a duct, and an effective diameter of the air inlet at the inducer portion of the compressor wheel is determined by a trailing edge inside diameter of the duct. The vanes are movable solely or in part by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel. The duct has a tapering configuration when the vanes are in a relaxed state, but under aerodynamic force the vanes flex outwardly and increase the trailing edge inside diameter of the duct, thereby increasing an effective diameter of the air inlet.