Abstract: A turbine-pump system bowl assembly for use with flowing liquid in a liquid conduit has an impeller subassembly that includes multiple axially abutting impeller members.

Abstract: A vertical-axis wind turbine apparatus is disclosed. In at least one embodiment, the apparatus provides a substantially vertically-oriented main shaft. A blade assembly is coaxially aligned with and rotatably engaged about the main shaft. The blade assembly provides an at least one blade radially projecting therefrom. A housing is rotatably engaged with the main shaft and configured for selectively encompassing the blade assembly. A first screen is integral with the housing and configured for shielding a return portion of the blade assembly. A second screen is rotatably engaged with the housing and configured for selectively moving between a retracted position, wherein the second screen is positioned substantially adjacent to the first screen such that a catch portion of the blade assembly is exposed, and a deployed position, wherein the second screen is rotated away from the first screen for at least partially shielding the catch portion from the wind.

Abstract: A pump for immersion in a fluid reservoir, such as a pit or lagoon containing liquid manure, from a position at an edge of the reservoir. The pump may be adapted for connection to a farm vehicle, such as a tractor, positioned at the edge of the reservoir. The pump comprises an extensible body, fluid conduit and drive means in order that a length of the pump may be varied in order to accommodate a variety of reservoir fluid heights. In addition, the pump may be pivotable relative to at least a portion of a frame in order that the entrance angle may be adjusted. The pump comprises a bottom housing with a bottom inlet and at least two tangential fluid outlets that are upwardly angled towards the conduit. A combiner is provided to merge the outlets with the fluid conduit. An impeller within the housing is shaped to transfer fluid tangentially and upwardly within the housing to co-operate with the upward angle of the outlets.

Abstract: A rotary shaft device (3) includes a shaft body (20) rotatably supported by angular bearings (35, 36), and a support body (40) configured to rotatably support the shaft body (20) via the angular bearings (35, 36). A ball rolling groove (21) having a Gothic arch shape in which rolling elements (39) of the angular bearings (35, 36) roll is formed in an outer circumferential surface of the shaft body (20).

Abstract: A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components. The invention furthermore relates to a method for producing such a brush seal system and to a thermal gas turbine having such a brush seal system.

Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.

Abstract: A system can include a shaft and turbine wheel assembly that includes a seal portion; a bearing assembly that includes an outer race and rolling elements that rotatably support the shaft and turbine wheel assembly; a sleeve that includes an outer diameter and a through bore that includes a first inner diameter that accommodates an outer diameter of the outer race of the bearing assembly and a second, smaller inner diameter that accommodates an outer diameter of the seal portion of the shaft and turbine wheel assembly; and a center housing that includes a compressor side, a turbine side and a bore that includes a turbine side bore diameter that accommodates the outer diameter of the sleeve.

Abstract: A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis.

Abstract: Shrouded turbine blisks and methods of manufacturing same are provided. A shrouded turbine blisk includes a central disk portion including an axis of rotation, an inner rim, a plurality of airfoils that extends radially outwardly from the inner rim; and a shroud integrally coupled to each of the plurality of airfoils. The shroud includes a plurality of circumferentially-arranged arcuate shroud segments defined at least in part by gaps positioned between adjacent shroud segments. The central disk portion, the inner rim, the plurality of airfoils, and the shroud are defined from a single billet of blisk material.

Abstract: An exhaust turbocharger has a wastegate valve and a thrust circulation valve, which can be actuated by a single, common actuator. The actuation of the thrust circulation valve is dependent on the positioning velocity of the actuator.

Abstract: An external actuator for a variable water pump is provided having an actuator housing with an outer wall with a plurality of radially inwardly directed projections, and a drive ring rotatably mounted in the housing. The drive ring has an internal thread. The projections contact an outer surface of the drive ring to define a plurality of hydraulic chambers that are divided by vanes extending from the drive ring into first and second chamber portions. A control valve controls a flow of pressurized hydraulic fluid to the chambers to rotate the drive ring in both directions or hold it in position. A drive nut having external threads is located within the drive ring and rotation of the drive ring causes an axial displacement of the drive nut. An actuator pin connected to the drive nut extends into the water pump housing to actuate the variable flow impeller.

Abstract: A seal assembly of an air cycle machine includes a seal plate with an outer diameter. A bore extends axially through a center of the seal plate and a seal land is disposed at least partially within the bore. The seal land includes an inner diameter and a minimum ratio between the inner diameter of the seal land and the outer diameter of the seal plate is approximately 0.1985.

Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.

Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.

Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.

Abstract: A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.

Abstract: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

Abstract: Length adjustable braces (56, 56A-D) attached between a gas turbine exhaust diffuser (40) and an exhaust casing (34) along a horizontal joint (50) between upper and lower halves (40A, 40B) of the outer diffuser shell. Brace lengths are adjusted to align bolt holes (52A, 52B) in respective bolt bosses (43A, 43B) on the upper and lower halves of the shell. The braces may be turnbuckles (56, 67) welded to or releasably attached at one end to the shell and at the other end to the casing. Exemplary fittings on the diffuser shell and casing for the brace ends may be clevis fittings (62) or eye fittings (72). The fittings may be configured to support both tension (58) and compression (59) of each brace. Two opposed fittings (70A, 70B) across the joint may be configured for insertion of a respective clevis bolt (63A, 63C) in both fittings from the same side.

Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.

Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.

Abstract: A turbine housing includes a turbine inlet plenum and a turbine housing body. The turbine housing body includes a turbine outlet mounting face, a seal plate mounting face, and a center bore formed between the turbine outlet mounting face and the seal plate mounting face. A first support is formed about the turbine inlet plenum and in contact with the turbine housing body. A relief pocket is formed in the first support proximate the seal plate mounting face. The relief pocket is formed at a first distance from a turbine housing center axis of the center bore and at a first depth relative to the seal plate mounting face. A ratio of the first distance to the first depth is between 2.66 and 2.90.

Abstract: A connector for coupling an exhaust manifold with a turbocharger housing may include a manifold coupling part coupled with the exhaust manifold, a housing coupling part integrally coupled with an end of the manifold coupling part and coupled with the turbocharger housing, and a plurality of exhaust gas paths penetrating through the manifold coupling part and the housing coupling part.

Abstract: A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange. The second plurality of fingers of the second flange is complementary to the first plurality of fingers extending from the first flange. The first flange and the second flange are coupled together in form-fitting engagement such that the first plurality of fingers and the second plurality of fingers form an interdigitated configuration.

Abstract: A ventilation assembly, particularly for a vehicle, has a cowl with a conduit for air flow. The conduit has a first portion and a second portion having a smaller diameter and a joining portion joining the first and second portions. A fan is disposed in the conduit. The fan has an impeller with a peripheral ring having a lip. An annular passage is formed between the ring and the conduit. The lip has a substantially frusto-conical shape; and the joining portion of the conduit has a substantially frusto-conical shape, with an inclination angle (?) at least approximately corresponding to that of the lip of the impeller. The inclination angle (?) is between 115° and 145°.

Abstract: This disclosure relates generally to fan shrouds for machine fans, and, more particularly, to the structure and design of double bell mouth shrouds and placement of double bell mouth shrouds relative to a machine fan. In some examples, a fan shroud encircling a circular fan having a plurality of fan blades can be provided. Some example fan shrouds can include an inlet adapted to receive air and an outlet adapted to outlet air. The inlet can include an inlet radius, and the outlet can include an outlet radius. In some examples, the outlet radius can each be about 10% of the fan diameter.

Abstract: A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

Abstract: An adjustable lift regulating device (30, 32, 40, 50, 52, 56, 60, 68, 72, 76) on an inboard portion of a wind turbine blade (28). The lift regulating device is activated to reduce lift on the inboard portion of the blade by causing flow separation (41) on the suction side (22) of the blade. To compensate for the lost lift, the blade pitch is increased to a running pitch that facilitates stalling on the outer portion of the blade in gusts. This provides passive reduction of fatigue and extreme loads from gusts while allowing full power production under non-gust conditions.

Abstract: A reverse wind load mitigation device (30) is provided for a wind turbine blade (20). The device (30) comprises a hinge member (32) attachable to a trailing edge (26) of a wind turbine blade (20). The separated flow inducer (34) is associated with the hinge member (32) and is configured to pivot about or with the hinge member (32) toward at least one of the surfaces (40, 42) in response to wind (45) traveling from a direction of the trailing edge (28). The separated flow inducer (34) is effective to induce flow separation (50) over at least one of the surfaces (40, 42).

Abstract: A paddle handle has a handle having a handle outside member connected to a handle inside member by a handle lateral member. A handle attachment member is connected to the handle at the handle inside member. A swivel is connected to the handle attachment member. The swivel has a first position and a second position. A first handle swivel detent and a second handle swivel detent are selectively engaged by a handle swivel engagement member. The first handle swivel detent is at a different angle than the second handle swivel detent. A handle swivel control is connected to the handle swivel engagement member. The handle swivel control is biased to engage into either the first handle swivel detent or the second handle swivel detent.

Abstract: Lightning protection system (LPS) with an integrated anti-icing system for wind turbine blades that comprises a smart protection system (10), an integrated IPS characterized by some conductive sheets (13) embedded in the carbon laminate of the wind turbine blade (1), some overvoltage dischargers (11) installed between the conductive sheets (13) of the IPS and the downlead cable (2) for the lightning protection system (LPS) and an external receptor frame (17).

Abstract: Provided is a ship propelling apparatus including a rotation shaft on which a rear propeller is fixed; a front propeller rotatably supported on the rotation shaft in front of the rear propeller; and a counter-rotating device through which the rotation shaft passes, which includes a gear box including therein a plurality of gears configured to reverse rotation of the rotation shaft and transfer the reversed rotation to the front propeller, and which is installed in an installation space formed at the rear of a ship. The rotation shaft includes a measurement hole formed to pass through a center of the rotation shaft for centering of the counter-rotating device installed in the installation space; and an individual lubricant path separated from the measurement hole.

Abstract: A bearing arrangement, comprising a rolling bearing, which includes an inner ring, an outer ring, rolling elements interposed therebetween, and a cage for holding and separating the rolling elements, wherein the inner ring presents an inner circumferential surface. A shaft is also present, wherein the rolling bearing is mounted on the shaft via the inner circumferential surface of the inner ring. The shaft during operation is meant to oscillate in its axial direction, or is positioned in an angle ? being (90?y) degrees, wherein y is between 0 and 89, or the rolling elements during operation are exposed of an axial force F, and the cage presents means for axially guiding the rolling elements against at least one of the inner ring, the outer ring or a separate element located outside the rolling bearing. The bearing can be integrated into a wind turbine main shaft arrangement.

Abstract: A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing. Frictional forces between contacting parts limit torsional windup and increase torsional resistance with increasing load. The damper bearing assembly includes a damper housing configured substantially within a U-shaped spring finger housing and a spanner nut with a radial hook portion coupled to the spring finger housing. The damper housing is coupled to the spring finger housing such that it is substantially confined within the U-shaped void. The spanner nut is coupled to the spring finger housing such that the radial hook portion is configured to limit the deflection of the spring finger housing and damper housing during a fan blade out event.

Abstract: An auger assembly according to one example embodiment includes an auger having a helical flight extending along a longitudinal axis. The auger has a central opening running along the longitudinal axis. The auger has an end that includes at least a portion of a turn having substantially zero pitch. A retaining member has a body including a groove on an outer surface of the body. The groove has a shape complementary to the helical flight at the end of the auger. At least a portion of the end of the auger is retained within the groove. A rotatable coupling member extends along the longitudinal axis. At least a portion of the rotatable coupling member is positioned within the central opening of the auger and presses the outer surface of the retaining member against an inner diameter of the end of the auger.

Abstract: Wind turbine (1) comprising a rotor (2) around a rotation shaft (3), having a plurality of blades (4) at a distance around the rotation shaft (3), in which the blades (4) can drive the rotor (2); a cavity (10) which extends between the ends (15) of the blades (4) closest to the rotation shaft (3); a plurality of vanes (5) around the rotor (2) for guiding wind to the blades (4), in which the vanes (5) extend from the ends (14) of the blades (4) furthest from the rotation shaft (3) to a second end (16) of the vanes (5). The vanes (5) and blades (4) merge into each other at the same curvature mathematically tangentially in a plane at right angles to the rotation shaft (3) and the curvature of the vanes (5) is described by a part of a logarithmic spiral.

Abstract: A shroud assembly having rope seals disposed between the shroud hangers and the surrounding case structure.

Abstract: A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

Abstract: A system for relieving stress on a turbine rotor blade dovetail in a gas turbine is provided. At least one turbine rotor blade includes a dovetail that is axially insertable into a correspondingly-shaped slot defined in a turbine disk. At least one axially-extending tang is defined on the dovetail. At least one stress relief surface is defined in the at least one tang. The at least one stress relief surface extends along a central portion of a length of the tang. Accordingly, contact between the at least one tang and an inner surface of the slot is precluded, along the central portion, such that stresses generated by radially-directed forces along the central portion are reduced.

Abstract: Prepregs and stacks of prepregs based on reactive epoxy resins that can be cured at lower externally applied temperatures such as from 70° C. to 110° C. with acceptably short cycle times comprise epoxy resins of epoxy equivalent weight from 200 to 500 containing a curing agent but no hardener.

Abstract: A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate outboard from the rim surface and contaminate the low-pressure zone, reducing propulsion. An outboard leading edge having an outboard sweep angle extends radially from the inboard leading edge to form an apex. The inboard and outboard sweep angles are each at least approximately 30 degrees and in the opposite direction. An inboard vortex forming near to and as a result of the apex trails circumferentially across the fan blades and is positioned to substantially confine the inboard flow regime to be inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan.

Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

Abstract: A beverage production module includes a pump for delivering a fluid from a tank to an extraction chamber, a power source for the pump and a controller for operating the pump and for controlling the voltage applied from the power source to the pump, wherein the controller is adapted to operate the pump at a normal operation voltage (U3) and to operate the pump over a predefined time (T1,T2) at a reduced voltage level (U1, U2). A method for operating the pump of a beverage production module is also provided.

Abstract: In at least one illustrative embodiment, a diaphragm pump may comprise a housing defining a first pumping chamber, a second pumping chamber, and a hydraulic fluid chamber, a first flexible diaphragm separating the first pumping chamber from the hydraulic fluid chamber, a second flexible diaphragm separating the second pumping chamber from the hydraulic fluid chamber, a rod mechanically linking the first flexible diaphragm and the second flexible diaphragm such that an expansion of one of the first and second flexible diaphragms exerts a contraction force on the other of the first and second flexible diaphragms, and a piston disposed within the hydraulic fluid chamber and configured to reciprocate to cause a hydraulic fluid contained within the hydraulic fluid chamber to alternately exert an expansion force on the first and second flexible diaphragms.

Abstract: A motor controller, including: a supporting frame, a control circuit board, and a control box. The control box includes: a cavity, a base plate, and a plurality of fins. The control circuit board is disposed on the base plate in the cavity. The fins are disposed outside the cavity on an outer side surface of the base plate. Cooling ducts are formed between adjacent fins. The control box is fixed on the supporting frame.

Abstract: Illustrative embodiments of a pump systems and methods are disclosed. In at least one embodiment, a pump system includes a main pump including an inlet and an outlet and configured to supply energy to a pumped fluid. The pump system further includes a booster pump fluidly coupled to either the inlet or the outlet of the main pump such that the pumped fluid flows through a pumping chamber of the booster pump whether the booster pump is active or inactive. The booster pump is configured to modify the energy of the pumped fluid when active and to allow the pumped fluid to flow through the pumping chamber without substantially modifying the energy of the pumped fluid when inactive.

Abstract: The Invention provided is a hydraulic powered down hole reciprocating pump traveling valve component to provided lifting hydraulics on the down stroke using the derived motion and pressure of petroleum liquids and gasses, such as oil, water and natural gas and also utilizing the frictional traveling forces driven by the surface equipment. Designed to utilize the elements within the pumping apparatus to obtain the hydraulic power within and transfer the energy's force to the exposed bottom end of the pressure locked traveling ball valve adjacent within the ball valve containment cage, providing ultimate lifting power to open the ball valve on the initiation of the down stroke. The component consist of a Hollow Hydraulic Power Shaft, Hollow Pressure Motion House, and a Fluid Cavity Power Drag Plunger.

Abstract: The subject matter described herein relates to a spin pump that includes a combination of a compressor and a vacuum pump on respective pistons extending from a common crankshaft in a rotating housing. Related methods, apparatuses, systems, techniques and articles are also described.

Abstract: An unconventional approach to propulsion provided by this invention incorporates 3 specific features making it possible to develop and maintain pressure at the intake nozzle upstream of the impeller to provide a second component to the overall propulsive effort thus converting the conventional jet drive into ramjet drive. At high speeds the second component becomes the prominent thrust, thus reducing the overall power demand to at high speeds to a third.

Abstract: A mechanical seal has a stationary face and rotating assembly adjacent to the stationary face. The rotating assembly includes an upper bellows ring, a lower bellows ring and a runner between the lower bellows ring and the stationary face. A bellows extends between the upper bellows ring and the lower bellows ring. In preferred embodiments, the bellows is constructed from a perfluoroalkoxy polymer and is secured within the upper bellows ring and the lower bellows ring by a selected locking mechanism. The locking mechanism may include the use of crimp rings configured for a press fit engagement within the upper and lower bellows rings. Alternatively, the locking mechanism may employ locking rings configured for threaded engagement with the upper and lower bellows rings.