Abstract: The invention relates to an outer turbine system (OTS) comprising an outer envelope having first and second ends with an axial inflow and a radial and/or axial outflow of a working gas or liquid. Inner turbine blades are disposed at an inner side of the envelope to rotate the turbine. The envelope and the blades can have a defined shape. The blades can be detachably attachable, adjustable, comprise hollow spaces. The envelope can comprise (adjustable) through openings. The turbine can be mounted in a housing, can include a defined feed casing and one or more stages. The turbine can be supported at defined portions, can be variably mounted, can work bidirectionally, can use regenerative power, can pump and can be fabricated from a defined material. The blades can be provided with a defined cooling system. The turbine can be coupled with another turbine, a mechanocomponent and/or an electrocomponent.

Abstract: A variable height fan of an information handling system includes a first fan having a first hub and a first plurality of fan blades. A second fan impeller includes a second hub and a second plurality of fan blades. The first hub slides along the second hub as the variable height fan transitions between an expanded position and a collapsed position. Interior edges of the first hub are in physical communication with exterior edges of the second hub, and the second fan impeller drives the first fan impeller through the physical communication between the interior edges of the first hub and the exterior edges of the second hub.

Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

Abstract: An engine defining a longitudinal axis includes: a turbomachine; a fan drivingly coupled with the turbomachine, the fan being a forward thrust fan and having: a hub; a plurality of fan blades, the plurality of fan blades comprising a first fan blade; and a flapping hinge integrated into the first fan blade or coupled to the fan blade, at least a portion of the first fan blade moveable about the flapping hinge to define a variable angle with the longitudinal axis.

Abstract: A fan including a housing having an air inlet and an air outlet. An impeller is disposed in the housing and driven by a motor connected thereto. A connecting mechanism is disposed on the housing in proximity to the outlet. The connecting mechanism is adapted for being mated with a respective connecting structure.

Abstract: A fan module including a body and a plurality of blades is provided. The body has a rotating axis and the body is telescopic along the rotating axis to have an elongated state and a shortened state. The blades are respectively disposed on the body and rotate along with the body along the rotating axis. At least a portion of each blade is flexible and a bending state of each blade is changed along with the elongated state or the shortened state of the body. An axial size of each blade along the rotating axis when the body is in the elongated state is greater than the axial size of each blade along the rotating axis when the body is in the shortened state.

Abstract: Gas turbine aircraft engine comprising an engine core comprising a turbine, a compressor, a core shaft connecting the turbine to the compressor; and a fan upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each fan blade comprises a main blade and an auxiliary blade. Over substantially all of the auxiliary blade's radial span, the leading edge of the auxiliary blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem.

Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.

Abstract: A variable geometry turbocharger includes: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor. The variable nozzle mechanism includes: a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction. Of an end surface of the nozzle vane on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape.

Abstract: A wind turbine is disclosed. The wind turbine includes a shaft rotatable about an axis, a plurality of hubs fixedly attached to the shaft, and a plurality of vanes. The vanes are releasably engaged with each of the plurality of hubs. The vanes disengage from the hubs once the shaft rotates about the axis at a cut-out speed of the wind turbine. In another embodiment, the vanes are releasably engaged with the shaft.

Abstract: One embodiment provides a fan, including: a hub for connection to a motor; and a plurality of blades coupled to the hub, the plurality of blades being mutually diverging from the hub and spaced apart around a common rotating axis, with each of the plurality of blades defining a centroid, wherein at least one blade of the plurality of blades is deviated with respect to a corresponding centroid of the at least one blade to provide a non-uniform arrangement of the plurality of blades while maintaining a respective centroid of the plurality of blades on a common circumference around the common rotating axis. Other aspects are described and claimed.

Abstract: A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.

Abstract: A turbine housing has a cavity that defines a turbine axis, and has a volute. The volute comprises a volute passage spiralling radially inwards towards the cavity, a substantially annular throat positioned around the cavity between it and the volute passage, and a tongue terminating at a distal tongue tip. In a plane containing the turbine axis and the tongue tip, the throat defines a line of minimum clearance, the volute passage and tongue tip co-operatively define a preliminary inlet area, and the tongue tip defines a tongue tip lateral centerline. The line of minimum clearance and the preliminary inlet area co-operatively define a line of passage offset, which connects the centroid of the preliminary inlet area and a point half way along the line of minimum clearance. The line of passage offset is not perpendicular to the turbine axis, and the tongue tip lateral centerline and the line of passage offset define an angle therebetween of at least 60 degrees.

Abstract: A gas turbine engine may have a blade receiver for holding a fan blade, wherein the blade receiver is rotatable about a radial axis of the gas turbine engine. The gas turbine engine may also include a variable pitch mechanism comprising an actuation arm. The gas turbine engine may also include a splined index ring disposed between the actuation arm of the variable pitch mechanism and the blade receiver. The splined index ring may include an outer spline and an inner spline.

Abstract: A gas injection blower includes a housing forming a box around the pump chamber, wherein the perimeter of the housing is also formed with a pump chamber communicating air inlet and an exhaust outlet, a fan shaft connected to a drive shaft the form of a rotatable type arranged in the pump chamber, the air inlet, forming a pressurized chamber of the pump flow passage between the fan and air vents and communicate with each other, the drive shaft extending through the shaft connected to a pump outdoor power source, wherein the drive shaft, at least between the inner wall of the frame around the blades and the pump chamber is formed a slit communicating the boost pressure drop of the flow channel, which is housing and forming a gap communicating the pressure drop gas injection passage; with the passage of gas injected into the inner injection cleaning gas pressure, to improve the traditional drop relatively easy accumulation of dust inside the gap problem.

Abstract: A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

Abstract: An annular casing for a rotor of a gas turbine engine includes a casing treatment having at least one groove defined in the annular casing wall with an open end defined in an inner surface of the annular casing wall, and a perforated sheet overlapping the open end of the at least one groove. The perforated sheet includes a plurality of apertures therethrough in fluid communication with the at least one groove. A method of reducing flow losses through a flow path having a rotor with a plurality of rotating blades extending therethrough is also presented.

Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

Abstract: A radiator fan of a motor vehicle, in particular a main fan, contains a fan wheel which has a hub and an electric-motor rotor which is attached thereto in a form-locking manner. At least one connecting dome is formed integrally on the rotor, which connecting dome protrudes through a corresponding cutout of the hub and is deformed on the free end side in a rivet-shaped manner in order to produce the form-locking connection.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.

Abstract: A refrigerator that includes a fan including a hub and a plurality of blades, the hub having a first accommodation space and the plurality of blades being disposed outside the hub; a motor including a stator and a rotor, the motor located in a case, the case having a cylindrical shape and being disposed in the hub, the stator being disposed in the case, and the rotor having a rotational shaft coupled to the hub and being rotatably disposed in the stator; and a support plate that is coupled to the case and that is configured to support the fan and the motor is disclosed.

Abstract: Fans having fan blade mounting structures are disclosed herein. A fan configured in accordance with one embodiment of the present technology includes a fan having a central hub coupled to a plurality of fan blades by a plurality of blade mounting structures. Each blade mounting structure can include first and lower support members that each extend toward an inboard end portion of an individual fan blade. Each of the upper and lower support members can include a first end portion coupled to the inboard end portion of the fan blade. Each of the upper and lower support members can also include a second end portion coupled to opposite sides of the central hub.

Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.

Abstract: Apparatus for generating energy in which an oscillating air column created by wave motion continuously drives a turbine in one direction.

Abstract: There is provided a turbine for a hydroelectric power plant comprising a hub, a plurality of turbine blades provided on the hub, a pitch angle adjusting unit coupled to the turbine blades for adjusting the pitch angle of the turbine blades, a double-acting hydraulic cylinder and a piston rod connected thereto. The piston rod is coupled to the pitch angle adjusting unit in such a way that the pitch angle adjusting unit performs a rotational movement when the piston rod is moved in the longitudinal direction. The double-acting hydraulic cylinder is provided in a hydraulic chamber coupled by way of a first and a second hydraulic line so that the double-acting hydraulic cylinder is displaceable by feed of a hydraulic fluid through the first or second hydraulic line and thus leads to adjustment of the pitch angle of the turbine blades by way of the coupling to the piston rod and the pitch angle adjusting unit.

Abstract: A turbine housing for an internal combustion engine, the turbine housing includes a coolant passage and exhaust gas flow path. The exhaust gas flow path is configured to pass exhaust gas of the internal combustion engine, a turbine wheel is arranged in the exhaust gas flow path, the exhaust gas flow path include a first portion, the first portion is disposed further on the exhaust gas downstream side than the turbine wheel in the exhaust gas flow path, and the inner diameter of the first portion gradually increases toward the exhaust gas downstream side.

Abstract: A casing for a blisk of a turbomachine including an internal coating made of an abradable material, and a plurality of circumferential slots arranged in the coating of abradable material, the casing further including a circumferential cavity formed in the coating of abradable material, into which cavity the slots open, the slots opening into the cavity and extending between the cavity and an internal surface of the casing. A turbomachine can include such a casing and a blisk.

Abstract: The invention is a rotating tip catheter-imaging probe where electromagnetic energy is delivered to the distal end of a catheter and converted to mechanical energy using a light drive apparatus. The mechanical energy is then used to rotate a mirror that redirects light in fixed pattern on a sample. The rotating element of the light drive apparatus contains vanes, which rotate about an axis and positioned with bearings to minimize friction. A chamber encompasses the rotating element and is set to a vacuum pressure. The rotational speed of the catheter tip can be controlled by varying the optical power delivered to the vanes, the vacuum pressure in the chamber, or by a braking mechanism applied to the rotating element. The vanes may be shaped in a particular geometry to increase forces on the vanes from thermally driven gas flow.

Abstract: A turbine casing is provided and includes first and second turbine casing shells configured to be removably coupled to one another. At least one of the first and second turbine casing shells is formed to define an access slot. At least one service wedge is configured to be removably installed in the access slot.

Abstract: A lift efficiency improvement mechanism is provided for use with a service wedge configured to be removably installed in an access slot of a turbine casing. The lift efficiency improvement mechanism includes a connector element, which is connectable with the turbine casing proximate to the access slot and a manually transportable lift efficiency improvement device, which is supportably coupled to the connector element and movably coupled to the service wedge. The lift efficiency improvement device is configured to urge the service wedge to move relative to the access slot responsive to corresponding operator control movement.

Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.

Abstract: A system for assembling a turbine engine component has a disk having a groove, which groove has a bearing surface and an upper wall, at least one locking slot being positioned at an intersection of the bearing surface and the upper wall; each locking slot having a shaped surface; and at least one lock having a shape which matches and mates with the shaped surface of the locking slot; and said locking slots providing clearance to assemble blades into the disk.

Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring. The device includes a rolling bearing including an inner cage slidably mounted on a turbine casing and connected to the rod of an actuator, and an outer cage that is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis.

Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).

Abstract: The present disclosure relates to an electric top bottom cleaner for pools or spas that includes internal pumps for suction and propulsion purposes. The pool cleaner includes a housing having a front end, a rear end, a first side, a second side, a bottom wall, and a top wall, with a first aperture extending through the bottom wall and a second aperture extending through the top wall. A tube extends through the housing between the first aperture and the second aperture. A debris retention mechanism is connectable to the housing. A first pump, a second pump, and a third pump are positioned within the housing.

Abstract: A fan module including a first fan, a second fan and a actuator is provided. The first fan has a first pivot portion and a plurality of first fan blades. Each first fan blade has a first blade face. The second fan has a second pivot portion and a plurality of second fan blades corresponding to the first fan blades. Each second fan blade has a second blade face. The second pivot portion is slidably disposed at a containing cavity of the first pivot portion. The actuator is adapted to drive the first fan to rotate. The first fan is adapted to drive the second fan to rotate. When the second pivot portion protrudes out of the containing cavity, a part of each of the second blade faces does not overlap with the corresponding first blade face along a direction perpendicular to the corresponding first blade face.

Abstract: One embodiment of a fan assembly includes a housing having a base member and a lip member extending outwardly from the base member for defining an enclosure. The fan assembly may further include a toothed track assembly, a wheel assembly, a first motor, a second motor, and a fan member. The toothed track assembly includes a toothed track member disposed within the enclosure. The wheel assembly includes a pair of toothed wheels adapted to move on the toothed track member. The first motor is operatively coupled to the wheel assembly and is capable of rotating the pair of toothed wheels. The fan member is coupled to the wheel assembly, such that the fan member moves along the toothed track member when the first motor rotates the pair of toothed wheels on the toothed track member. The second motor is operatively coupled to the fan member for rotating the fan member.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: A fan configured for integration with a structure having at least two support members is disclosed. The fan comprises a fan guard, a fan blade surrounded by the fan guard, and first and second mounting brackets. Each of the first and second mounting brackets is configured for connection to a respective one of the support members. The fan also comprises first and second connectors oppositely disposed on the fan guard and configured for connection to a respective one of first and second mounting brackets. The first and second connectors are adjustable with respect to the first and second mounting brackets, and the fan is configured to rotate between at least two struts. Rotation of the fan between the at least two struts is limited such that an opening defined by one of the struts and said fan guard does not exceed a predetermined size.

Abstract: A turbine balance assembly has a turbine rotor and shaft. Bearings are positioned radially outwardly of the shaft. A bearing sleeve is positioned radially outwardly of the bearings, and supports the bearings. The bearing sleeve extends along an axial length defined by a rotational axis of the shaft, and has a turbine rotor end adjacent to the turbine rotor, and a remote end. A radially outwardly extending flange on the bearing sleeve extends radially outwardly of a support portion of the bearing sleeve at the turbine rotor end. The flange has a nominal outer diameter, and includes a slot for receiving an anti-rotation tab from a gear cage over a first circumferential extent. A bearing sleeve incorporates the anti-rotation feature, and a gear cage incorporates its portion of the anti-rotation feature. An air turbine starter, and a method of installing components of a turbine balance assembly are also disclosed.

Abstract: A power generation device for a vehicle comprises a housing adapted to removably affix to a rear of a vehicle and a rotatable support member for rotatably supporting a first device, the rotatable support member operatively connected to the housing, wherein the first device includes rotor blades for producing electrical energy when exposed to a flow of air. Further, the rotatable support member is adapted to be articulated between a range from a first position, wherein the rotatable support member and the rotor blades of the first device are disposed within the housing, and a second position, wherein the rotatable support member and the rotor blades of the first device are disposed outside of the housing.

Abstract: A method for repairing a hub pitch gear assembly. The method includes providing a ring assembly for adjusting a pitch angle of a wind turbine blade having a plurality of gear teeth. A segment of the ring assembly is removed, the segment including at least a portion of at least one gear tooth, to form a repair cavity. A repair segment configured to mate the repair cavity is provided and the repair segment is directed into the repair cavity and fastened in position. A repaired pitch gear assembly and wind turbine are also provided.

Abstract: A compressor is disclosed. The compressor has at least one guide vane assembly which can be adjusted to change the outflow angle, and a rotor which is connected downstream of the guide vane assembly. The guide vane assembly and rotor are arranged between a housing and a hub of the compressor. The guide vane assembly is divided in the direction of extension from the housing to the hub into two or more sections which can be radially adjusted relative to one another, or has a clearance radially in the direction of extension, the clearance allowing a substantial amount of flow to pass.

Abstract: A propulsor and control system for an underwater vehicle (35) having annular fore and aft circumferential shrouds (4 & 5) surrounding the hull (2). The fore and aft circumferential shrouds (4 & 5) form respective fore and aft circumferential shroud gaps (6 & 16) between the fore and aft circumferential shrouds (4 & 5) and the hull (2). Fore and aft propulsor blades (7 & 17) are situated substantially or completely within the fore and aft circumferential shroud gaps (6 & 16); the blades counter-rotate in one preferred embodiment. The fore or aft circumferential ring propulsors (2 & 3) can have front control vanes (13 & 22) located in front of the respective propulsors, and back control vanes (11 & 22) located behind the respective propulsors to control the direction of the flow of water in order to maneuver the underwater vehicle (35). Other embodiments are shown.

Abstract: A housing for an axial-flow fan includes a frame, a seat and a plurality of stationary blades. The frame has an air inlet and an air outlet. The seat is received in the frame and at a position where the air outlet is formed. Two ends of each stationary blade are respectively fixed to an outer periphery of the seat and an inner periphery of the frame. Furthermore, extending directions of any two adjacent stationary blades jointly define an included angle, and all of the included angles formed by all of the stationary blades are of more than two values in degrees, so that the stationary blades are not spaced with equal intervals. Consequently, while sucked air passes by the stationary blades, noises with the same tone can be suppressed effectively.

Abstract: A turbomachine includes a compressor having a compressor intake, and an intake system mounted upstream of the compressor intake. The intake system includes a housing and a plurality of selectively positionable vanes arranged within the housing. The plurality of selectively positionable vanes are moveable between a first position to remove a first amount of foreign particles, and a second position, to remove a second amount of foreign particles.

Abstract: Vertical axis turbine apparatus is described in which a rotating blade turbine member mounted on a fixed base includes one to fifty, preferably two or three, upwardly and outwardly inclined spars. On each spar is set at least one aerofoil or hydrofoil section blade. If there is more than one spar, the spars are preferably held to one another via a plurality of guy wires.

Abstract: A fan system is disclosed having a forward fan stage configured to pressurize an airflow and an aft fan stage having a tip-fan configured to pressurize a first portion of a pressurized air flow from the forward fan stage wherein the aft fan stage is driven by a second portion of the pressurized airflow.

Abstract: The invention is intended to maintain turbine reliability when, based on a gas turbine designed for one desired cycle, a gas turbine for another different cycle is manufactured. A channel of a compressor is formed such that a mass flow of a fluid compressed by the compressor changes. Thus, when manufacturing, based on the gas turbine designed for one desired cycle, the gas turbine for another different cycle, turbine reliability can be maintained.