Abstract: A mechanical coolant pump for an internal combustion engine includes a pump rotor wheel comprising rotor blades configured to pump a coolant radially outward. A non-rotating ring of pump stator blades is configured to encircle the pump rotor wheel. At least one of the pump stator blades is a static blade. At least one of the pump stator blades is a pivotable blade configured to pivot about a pivot axis arranged within the pivotable blade.

Abstract: A bumper assembly includes a bracket and a pad. The pad is connected to the bracket by a first rivet. Additionally, a synchronizing ring assembly for a gas turbine engine includes a ring section and a bumper assembly. The bumper assembly is connected to a side surface of the ring section and extends axially adjacent an inner radial surface of the ring. The bumper assembly is disposed adjacent a gap at an end of the ring section.

Abstract: In a turbine for an exhaust gas turbocharger having a turbine housing including a turbine wheel with blades, each having a leading edge and a trailing edge, an adjusting device is provided controlling the flow to the leading blade edges of the turbine wheel and also a device for controlling the flow from the trailing edges of the turbine wheel blades, both devices are coupled to one another so as to be adjustable by a single actuator.

Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.

Abstract: A system can include a linkage that includes a turnbuckle component fixed between extensions of a rod end, a turbine assembly that includes a rotatable wastegate poppet arm connected to a pivotable wastegate valve control arm coupled to the rod end of the linkage by a peg, and an actuator that includes a translatable rod connected to the turnbuckle component of the linkage to pivot the wastegate valve control arm and rotate the wastegate poppet arm. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A variable vane actuation system with a plurality of vanes which may be rotated to change an approach angle of associated airfoils. A cylinder drives a piston rod to in turn cause a linkage system to vary the approach angle of the airfoils. The cylinder has a tailstock at an end remote from the piston rod. A spherical bearing mounts the tailstock. A bearing retainer provides a stop to prevent undue rotation of the tailstock relative to the bearing. A compressor and a gas turbine engine are also disclosed.

Abstract: Disclosed are systems and method that generally relate to the capture of wind energy by small wind turbines mounted on buildings with gabled roofs. Wind energy harnessing system for gabled roof buildings having a roof ridge including a low silhouette visually appealing enclosure mounted along the roof ridge of a building and extending down both sides of the roof forming the ridge. The enclosure includes airflow guides defined by columns extending down a length of both sides of the building roof forming sidewalk and a roof formed of pivoting louvers above the columns. A paddle-wheel type wind turbine consists of a multiple-bladed cylindrical shaft that contacts the wind and provides rotational work mounted within the enclosure and a generator connected to the wind turbine for converting the rotational work. from the wind turbine to electrical energy. The enclosure for the wind turbine functions to capture wind and directs the airflow via the airflow guides before it reaches the ridge.

Abstract: A regulatable coolant pump and a method for regulation of this regulatable coolant pump for internal combustion engines, which is driven by way of a pulley actives a valve slide using an electromagnetically activated piston pump equipped with a return spring in the form of a pressure spring. The pump implements a “pump feed” using many small “partial lifts.” A “leakage volume stream” that flows opposite to the “pumped volume stream” is superimposed on the “pumped volume stream” via the arrangement of circular apertures both in the inlet valve membrane of the working piston and in the outlet valve membrane so that the valve slide can be moved in defined manner and in a very robust and reliable manner, with low drive power via the defined superimposition of these two volume streams.

Abstract: A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.

Abstract: A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate.

Abstract: An example method of controlling a flow enhancement device includes providing a flow enhancement device that is configured stabilize a flow of air near a nacelle. The flow enhancement device has a first setting and a second setting that provides more stabilization than the first setting. The method includes monitoring parameters of a turbomachine to determine the stability of the flow of air near the nacelle. The method also adjusts the flow enhancement device between the first setting and the second setting based on the monitoring.

Abstract: A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.

Abstract: An apparatus for sealing a gap between a stator vane platform including a seal slot, and a rotatable stator vane including a shaft connected to a vane end. The apparatus includes a substantially flat, semi-annular seal body, a first tab and a second tab. The seal body extends circumferentially between a first body end and a second body end, and radially between a radial inner body side and a radial outer body side. The inner body side wraps partially around the shaft, and the outer body side mates with the seal slot. The first tab extends axially from the first body end, and the second tab extends axially from the second body end. The first tab and the second tab engage the vane end and cause the seal body to move within the seal slot during rotation of the stator vane.

Abstract: A turbine assembly for generating electricity from kinetic energy of a moving fluid flow. The turbine assembly includes an elongated casing defining a fluid channel through which the fluid flow is allowed to travel, as well as an inlet and an outlet for respectively receiving and releasing the fluid flow to and from the fluid channel. The assembly also includes a main rotor contained within the casing and intersecting the fluid channel, the main rotor being rotatably moveable with respect to the casing via a pivoting component. The main rotor has a closed-loop arrangement provided with a plurality of rotor vanes each defining a neighbouring closed-loop rotor passage, the main rotor being rotatably driven via the passage of fluid flow through its closed-loop arrangement, and the closed-loop arrangement being further configured for imparting a forced rotational movement to the fluid flow exiting from the main rotor.

Abstract: An assembly includes a fixture, first and second vanes, and an insert. The first vane and the second vane are retained within the fixture and are spaced at a distance from one another. The insert is disposed between the first vane and the second vane and the insert includes a spring that exerts a force that is applied to both the first vane and the second vane.

Abstract: A refrigeration compressor is provided and may include a shell carrying a suction-inlet tube having an outlet nozzle opened to the interior of the shell and a cylinder block to which is mounted a suction muffler that incorporates an admission tube provided with an inlet nozzle. The inlet nozzle of the admission tube may be disposed adjacent to the outlet nozzle of the suction-inlet tube. The inlet nozzle may admit—under at least one of the conditions of underpressure in its interior or deflection of the refrigerant-fluid flow in the interior of the shell the gaseous phase and may direct the liquid phase to a region of the shell external to the inlet nozzle.

Abstract: In a turbine of an exhaust gas turbocharger an insert element which is provided for insertion into a turbine housing has a spiral port which extends in the circumferential direction of the insert element over at least part of the circumference thereof and by which the exhaust gas flow through the turbine is controlled. The insert element is open in the axial direction on at least at one end face thereof which end face is biased in sealing contact with the turbine housing. The insert element has a central axial opening with a spiral port for accommodating a turbine wheel.

Abstract: A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.

Abstract: An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communication the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.

Abstract: This invention relates to a turbine for extracting energy from an oscillating working fluid. The turbine includes a housing defining a flow passage for the working fluid. An energy conversion unit is disposed in the housing. Flow control means is selectively movable to occlude a predetermined portion of the flow passage such that the working fluid is directed to act on a certain section of the energy conversion unit.

Abstract: Embodiments related to wind turbines and methods of guiding a flow of a fluid using a wind turbine. In one embodiment, a wind turbine includes a framework including an annular upper guide means and an annular base guide means; and an annular rotor assembly surrounding a central space, the rotor assembly comprising a plurality of rotor vanes, each rotor vane being held in position between the upper guide means and the base guide means.

Abstract: Various systems for processing air are disclosed. In one embodiment, an air processing system includes: an inlet manifold adapted to receive compressor discharge air from multiple turbine compressors; an air processing system fluidly connected with the inlet manifold, the air processing system adapted to process the compressor discharge air to provide a processed working fluid; an outlet manifold adapted to provide the processed working fluid to multiple turbine inlet filtration system; and a control system operably connected to the inlet manifold, the air processing system and the outlet manifold, the control system configured to control flow of the compressor discharge air from the multiple turbine compressors to the inlet manifold.

Abstract: A fluid flow machine has a main flow path in at least one stage, with a rotor arrangement and a stator arrangement, resulting in an increased rotor-stator constriction ratio QRS, which satisfies the following equation: [0.2+(KT?0.45)0.1]<QRS, with QRS being defined to the following formula: QRS=KR/KS with KT being the total stage constriction, and with QRS and KT being determined as follows: QRS=KR/KS with KR=ARI/ARA and KS=ASI/ASA KT=ARI/ASA with ARI, ARA, ASI and ASA being calculated as follows: ARI=?(R22?R12) ARA=?(R42?R32) ASI=?(R62?R52) ASA=?(R82?R72).

Abstract: A variable guide vane assembly comprising a variable guide vane having an aerofoil and a spindle at one end of the aerofoil; wherein the vane further comprises a platform positioned between the aerofoil and the spindle, the platform having a surface facing in the direction of the spindle and at least one side face; the assembly also having a washer with an aperture through which the spindle extends, the washer having a portion which overhangs the at least one side face.

Abstract: The present invention relates to a stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least two radial planes, as well as at least two stator vane adjusting rings connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device, characterized in that the actuating device is connected to the stator vane adjusting rings by means of a first transmission device and that a second transmission device, which is not coupled to the actuating device, is arranged essentially opposite to the first transmission device, with the second transmission device being connected to the stator vane adjusting rings.

Abstract: The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles.

Abstract: A variable vane assembly includes a damper positioned between a platform and a trunnion. The damper is comprised of a resilient material.

Abstract: An apparatus (10) for generating electrical power from wind energy (20) comprising: means (22) for forming at least two discrete jets of air (24) from an oncoming wind (20); a conduit (16); and at least one wind electricity turbine (14) located within the conduit (16), wherein the jets (24) are arranged to enter the interior of the conduit (16) from different directions and to converge towards a point or points (20) located within the conduit (16).

Abstract: A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.

Abstract: An integrated assembly includes a vehicle bumper system, and upper and lower air shutter sections with subassembled shutter vanes movable between closed and open positions, an actuator mechanism for moving the shutter members between positions. When in the fully open position, the shutter vanes are aerodynamically designed to minimize air drag, both as air flows past the vanes and also during after-vane airflow (and during after-bumper-beam airflow). When in the fully closed vane position, the vanes seal against each other to provide a highly efficient and leak-resistant air-blocking assembly.

Abstract: An axial compressor is provided. The compressor has an annular flow channel, in which adjustable blades of a blade ring that extend through the flow channel are rotatably mounted. Each blade has a lug on the rotor-side of the vane for mounting an inner ring. In order to provide a wear-free, self-centering inner ring, the ring is designed as a split ring with two opposing ends and a spring element for spreading the split ring.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser that includes an elliptical plate including multiple vane receptacles disposed about an axis of the plate and multiple detachable vanes attached to the plate. Each vane receptacle includes a first two dimensional (2D) projection along a plane of the elliptical plate and each detachable vane includes a second two dimensional (2D) projection along a base portion of the vane, where each detachable vane is disposed in a respective vane receptacle with the first and second 2D projections blocking movement of the detachable vane in at least a first axial direction relative to the elliptical plate. In certain embodiments, the first and second 2D projections may include a first tab to fit in a recess between a pair of second tabs, respectively, or vice versa. However, in other embodiments, the first and second 2D projections may include alternative mating surfaces.

Abstract: An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream.

Abstract: System and method for converting kinetic energy from a fluid flow into mechanical energy, the method comprising the steps of: a) providing a turbine including first and second hydrofoils, each of the hydrofoils being able to move lin-early in a heaving motion, and being able to oscillate about a spanwise axis in a pitching motion, said heaving and pitching motions being quasi-si-nusoidal, b) coupling the heaving motions of the first and second hydrofoils to the pitching motions of the second and first hydrofoils respectively, with the pitch-heave motion phase being substantially equal to the inter-hydrofoil phase, the heaving motion of one of the hydrofoils thereby driving the pitching motion of the other hydrofoil; and c) transforming the heaving motions of the hydrofoils into a rotational movement of a rotatable shaft, with linear-to-rotary transmission means.

Abstract: An assembly can include vanes and a base configured to seat the vanes at a radial distance about an axis where each vane includes a leading edge and a trailing edge, a pair of lateral surfaces that meet at the leading edge and at the trailing edge, an extension that extends from one of the lateral surfaces and that has a contact surface, and a stop surface to form a contact with a contact surface of another vane to define a minimum flow distance between the vane and the other vane. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: It is disclosed that a power steering pump. Which is characterized in that the front oil distributing plate is enclosed with front wall of the inner cavity of the pump body to form a front outlet cavity, a valve bore being formed at outer circumference side of the inner cavity of the pump body communicates with the front outlet cavity, a flow securing control valve is disposed within the valve bore, the front outlet cavity communicates with an oil outlet hole at the front portion of pump body through a high-pressure oil passage. The invention adopts a front high-pressure cavity configuration of the pump body to shorten the length of high-pressure oil passage, which hence avoids steering pump failure caused by aggressive overheating generated in the traditional configuration with excessive length of the flow passage and bending.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A recirculation fan includes a casing, a covering member, a wind-guiding device, a passive impeller, and an active impeller. The covering member is coupled with the casing to define an accommodation space. The wind-guiding device is disposed on the covering member, and includes a wind-guiding cover and a magnetoresistive structure. The magnetoresistive structure is disposed on the covering member and the wind-guiding cover. The passive impeller is disposed within the accommodation space. The active impeller is disposed within the accommodation space and located beside the passive impeller for generating a wind to drive rotation of the passive impeller and the wind-guiding cover. In response to a magnetic torque resulted from a magnetic vortex of the magnetoresistive structure, a rotating speed of the wind-guiding cover is slowed down.

Abstract: A control device for controlling pivotable vanes of a turbo-machine, including: a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; and a control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links; wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with other links being connected to the ring portion via respective sliding pivot connections.

Abstract: A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.

Abstract: Non-uniform variable stator vanes for a single stage of a gas turbine engine stage include non-uniform airfoils with a non-uniformity between airfoils of first and second portions of the stator vanes. The variable stator vanes may further include all outer buttons, from which the airfoils inwardly extend, in all of the variable stator vanes being equally sized and shaped and the same all inner buttons if used. The airfoils in the first and second portions may be counter-clockwise and clockwise biased respectively with respect to a nominal airfoil position. The airfoils in the first and second portions may be counter-clockwise and clockwise leaned respectively with respect to the nominal airfoil position. Outer ends of the airfoils in the first and second portions may be counter-clockwise and clockwise shifted respectively with respect to the nominal airfoil position.

Abstract: A wind power system including a wind turbine affixed to a support tower, and a wind deflector deployable relative to a direction of air flow and configured to control the movement of at least a portion of air flow passing through rotor blades of the wind turbine to reduce wind loads on the components of the wind turbine while maintaining the air flow in an operating power production range.

Abstract: A priming valve for priming a centrifugal pump includes a valve assembly separating an inlet chamber from an outlet chamber. The inlet chamber is fluidly coupled to an intake for the centrifugal pump and the outlet chamber is fluidly coupled to a priming pump. A control valve is provided to operate the valve assembly in order to fluidly connect the inlet chamber with the outlet chamber. While the valve assembly fluidly connects the inlet chamber with the outlet chamber, the priming pump can operate to replace air in the intake and the centrifugal pump with water.

Abstract: A device for adjusting variable guide vanes of an axial-flow machine includes a control rod that adjusts an angular position of the variable guide vanes and is pivotably connected to a shaft. Each of a first and a second bracket has a first end connectable to a casing of the machine. A first joint is fixed to a second end of the first bracket and provides adjustable positioning of a first end of the shaft. A second joint is fixed to a second end of the second bracket and provides adjustable positioning of a second end of the shaft. The two joints are spatially positioned to each other solely via a first fixed connection between the first end of the first bracket to the casing and via a second fixed connection between the first end of the second bracket to the casing.

Abstract: An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.

Abstract: A pump having an insert between an impeller and diffuser, where the insert includes an annulus that is in communication with fluid flow passages in the impeller and diffuser. The passages and annulus define a fluid flow path through the pump. Vanes are provided in the annulus that can pivot and vary the cross sectional area of the fluid flow path. Regulating the fluid flow path area alters the flow rate where the pump operates at its maximum efficiency. Thus by monitoring flow through the pump, the vanes can be adjusted so the flow rate of maximum efficiency corresponds to the actual flow rate.

Abstract: An example nacelle assembly for a gas turbine engine includes a nacelle defined about an axis and defining a boundary of a fan bypass flow path. A fan variable area nozzle includes a plurality of inserts movably mounted to said nacelle. Each of the multiple of inserts is located at a circumferential position about the nacelle. The multiple of inserts are each independently moveable into the fan bypass flow path relative the nacelle to selectively vary a fan nozzle exit area.

Abstract: A flow control module for a turbomachine includes an inlet extending to an outlet through a flow passage having at least one side wall. A flow control member is arranged within the flow control module. The flow control member is secured to the at least one side wall between the inlet and the outlet. The flow control member is selectively passively activated to extend into the flow passage to block cooling fluid passing through the flow control module.