Abstract: A method of making a fan having one or more dust-resistant surfaces comprises the steps of: providing (S50) an open mold for injection-molding purposes, having a cavity (43) corresponding to the desired configuration of fan components to be formed; wetting (S52) the surface of the cavity (43) with a mixture (24) of nanoparticles (19) and a solvent carrier; evaporating (S54) said solvent carrier, thereby depositing said nanoparticles on the wall of the cavity (43); closing (S56) the injection mold (10, 12); injecting (S58) thermoplastic (42) into the cavity (43); permitting the thermoplastic to harden, thereby binding the nanoparticles into the surface of the thus-created component(s), and removing (S60) the completed component(s) from the mold, for subsequent assembly as part of a fan.

Abstract: A power generation system that includes a heat source loop, a heat engine loop, and a heat reclaiming loop. The heat can be waste heat from a steam turbine, industrial process or refrigeration or air-conditioning system, solar heat collectors or geothermal sources. The heat source loop may also include a heat storage medium to allow continuous operation even when the source of heat is intermittent. Heat from the heat source loop is introduced into the heat reclaiming loop or turbine loop. In the turbine loop a working fluid is boiled, injected into the turbine, recovered condensed and recycled. The power generation system further includes a heat reclaiming loop having a fluid that extracts heat from the turbine loop. The fluid of the heat reclaiming loop is then raised to a higher temperature and then placed in heat exchange relationship with the working fluid of the turbine loop. The power generating system is capable of using low temperature waste heat is approximately of 150 degrees F. or less.

Abstract: The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off.

Abstract: The invention relates to an assembly for a stator stage of a turbomachine, the assembly comprising: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of said openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening. The invention is applicable to the stator stage of an axial compressor or a turbine of a turbomachine.

Abstract: A ventilation fan includes a rotor holder rotating around a rotation axis, an impeller cup including a plurality of blades provided on an outer circumference thereof, and a base portion arranged to rotatably support the rotor holder through a bearing portion. The base portion includes an outer circumferential wall extending upwards in an axial direction from an outer circumferential edge portion thereof. A gap defining a labyrinth structure is provided between an upper end portion of the outer circumferential wall of the base portion and a lower end portion of an outer circumferential portion of the impeller cup. A lower end portion of a cylindrical portion is located axially lower than the upper end portion of the outer circumferential wall of the base portion.

Abstract: The invention relates to an exhaust manifold (18) of an interna! combustion engine (20), with a number of exhaust pipe bends (1) corresponding to the number of cylinders of the internal combustion engine (20), said exhaust pipe bends being brought together at one end into an input flange (2) which can be fastened to the internal combustion engine (20), and being brought together at the other end; with a supply gas duct (21) which is connected at one end to a collector component (4) and at the other end to a rotor space (15) of a turbine housing (17) of a turbine of an exhaust-gas turbocharger; and with at least one compensator (19?) for compensating for thermal stresses in at least one exhaust pipe bend (1) and the supply gas duct (21), wherein the at least one compensator (19?) is designed as a component which is integrated in at least one exhaust pipe component (1).

Abstract: In a steam turbine according to a first embodiment, an outer casing 11 is divided into an upper casing 31 and a lower casing (a lower block) 32 on a horizontal plane through which a rotor passes, and the upper casing 31 is divided into a middle block 33 having a through hole 20 and an upper block 34 having a top panel 31a, that is, into a portion including at least a part of the through hole 20 through which the rotor penetrates and other parts. With this configuration, machining of a bellows fitting unit provided in an end-plate cone portion 21A can be performed in existing facilities such as a factory, in a state that the lower block 32 and the middle block 33 are assembled without assembling the upper block 34.

Abstract: Axial-flow compressor including, within a compressor casing (4), at least one rotor (2) of rotor blades (3) connected to a drive shaft (1) and a stator (5) held on the casing inner wall and, associated to the rotor gap (6) between the blade tips and the casing inner wall, a flow pulse generator (7) for stabilizing the rotor gap flow, characterized in that the flow pulse generator (7) includes pulse channels (7a) arranged on the inner wall of the casing and extending upstream of the rotor (2) and tapering in flow direction to accelerate the wall-near flow (9), with the shape and size of the pulse channels (7a) being determined by circumferentially spacedly disposed, successive separators (7b) attached without gap on the compressor casing inner wall. The flow pulse generator (7) so designed, which is easily manufacturable, improves the stabilization of the rotor gap (6) flow, extends the operating range of the compressor and increases the surge limit.

Abstract: A gas turbine housing component includes a wall structure including two adjacent wall parts and a connection arrangement arranged between adjacent edges of the two wall parts. The connection arrangement includes an elongated seal strip positioned along the wall part edges and bridging the distance between the wall part edges.

Abstract: The present invention relates to a compact fan, comprising a fan wheel, in particular a radial fan wheel (1), which is fastened on a rotor of an external rotor motor (82). The fan wheel (1) is supported between a front plate (8) having an air inlet opening (9), which is central, and a motor mount (11). The front plate (8) and the motor mount (11) are connected to one another via multiple spacers (12), which are disposed around the circumference. The front plate (8) and the motor mount (11) are formed as plastic or metal spray parts. The spacers (12) are formed as plastic or metal parts entirely or partially in one piece to the front plate (8) and/or the motor mount (11).

Abstract: New devices and methods for the construction of large Flow Deflection Devices (FDDs) are presented.

Abstract: The invention relates to a nacelle (100) for the turbojet of an aircraft that comprises a downstream structure including: an outer structure (106), a concentric inner structure (109) surrounding a downstream portion (111) of the turbojet and including an upstream section having a relatively small diameter (113) and a downstream section having a relatively large diameter (114), wherein said inner structure (109) defines together with the outer structure (106) an annular flow channel (108); and a guiding system (140) for connecting the inner structure (109) and the downstream portion (111) of the turbojet engine or a portion of a suspension mast; characterised in that the guiding system (140) includes a means for combining a translation and rotation movement of at least a portion of said inner structure (109) between a working position, in which the inner structure (109) is used as a cowling for the turbojet downstream portion (111), and a maintenance position in which the inner structure (109) exposes said tur

Abstract: A transition duct for conveying hot combustion gas from a combustor to a turbine in a gas turbine engine. The transition duct includes a panel including a middle subpanel, an inner subpanel spaced from an inner side of the middle subpanel to form an inner plenum, and an outer subpanel spaced from an outer side of the middle subpanel to form an outer plenum. The outer subpanel includes a plurality of outer diffusion holes to meter cooling air into the outer plenum. The middle subpanel includes a plurality of effusion holes to allow cooling air to flow from the outer plenum to the inner plenum. The inner subpanel includes a plurality of film holes for passing a flow of cooling air from the inner plenum through the film holes into an axial gas flow path adjacent to the inner side of the inner subpanel.

Abstract: A shrouded wind turbine includes a shroud with an exterior surface that includes a smooth outer surface. The smooth outer surface is large enough that additional devices, particularly advertising displays or solar panels, can be mounted to the shroud to more efficiently use available surface area, both on the wind turbine itself and on the footprint of the wind turbine.

Abstract: A device that converts gravitational energy into electricity using the weight of a vehicle with a hydraulic turbine transmission that dissipates the acceleration into the generator while the vehicle drops at a fixed, constant speed, represented by Newton's 2nd Law of Motion; the resulting electrical power generated being used for utility use on the surrounding municipal power grid and the structure, a multiple story parking garage, it operates in. The turbine and generator are combined into one unit; the blades, which variate in pitch according to speed and torque are affixed to the field rotor of the generator, which acts as a flywheel and rotates around the armature rotor, which is rotated in the opposite direction by the fluid pump shaft, generating the electrical power. Hydraulic pressure comes from a fluid pump that is turned by cables with one end attached to a platform, the other end attached to slightly heavier counterweights.

Abstract: A blower housing of novel two-piece construction is comprised of first and second housing parts of stamped or drawn sheet metal that are attached together. The two-piece construction provides the housing with two interior portions separated by an interior wall. The interior wall has an opening that is spaced from the aligned exhaust opening of the heater and the output opening of the housing. This creates a winding exhaust gas flow path through the blower housing. The interior wall is also provided with a recessed cavity that receives a portion of a fan rotated by a motor supported by the blower housing. Positioning of at least a portion of the fan in the cavity reduces the overall height dimension of the blower housing and facilitates the retrofitting of the blower housing between an existing exhaust opening of a heater and an axially aligned flue pipe.

Abstract: A water pump may be provided with a pump housing and a reservoir. The reservoir may have a first portion integral with the pump housing and a second portion manufactured as a separate part. The second portion has an internal volume which is in fluid communication with the first portion. A method is disclosed in which a fluid is drawn into a pump housing and pressurized. Some of the fluid is forced past a seal and collected in a part of a reservoir coupled to the pump housing. That reservoir part is heated to evaporate the fluid.

Abstract: A fan unit holds a cooling fan and is detachable from a main body of an inverter apparatus. The fan unit is provided with a fan-unit retainer plate having keyhole-shaped apertures and provided between an upper case and a lower case. The fan unit is fixed by pressing the fan-unit retainer plate with fixing screws. The fan unit is easily and reliably removed by moving the fan-unit retainer plate without directly moving the fan unit and without removing the fixing screws.

Abstract: Metal plated organic polymer compositions are useful as vehicular turbochargers components. Such components may have lighter weight, and/or superior corrosion resistance, and/or be more easily fabricated than conventional turbocharger components.

Abstract: A turbine system having a series of uprights or fingers disposed about the inner surface of a rotating ring having turbine blades disposed within the ring. As the turbine blades are motivated by water movement, the fingers or uprights cause increased power by increasing the flow characteristics of the turbine system. The uprights can be of a variety of lengths and may be directed toward the central hub of the turbine or pointed at angles to the hub. Alternatively, the uprights may be bent on the end or curved to create a vortex into the main turbine blades.

Abstract: A blade (31) of a turbomachine, especially of a steam turbine, is characterized in that the chord length (sm) in the middle region of the blade airfoil (34) is shorter than the chord lengths (s0, s1) in the tip-side region (35) or root-side region (33) of the blade airfoil. As a result of this, a distribution of the Zweifel parameter over the longitudinal extent of the blade airfoil is achieved which minimizes the losses of a blade cascade of the proposed blades.

Abstract: A wind turbine has an impeller surrounded by a shroud. The shroud is formed from inflatable components extending between two rigid structural members. When inflated, the shroud acts to increase the energy generated by the impeller. Under adverse wind conditions, the inflatable components can be deflated to reduce surface area and wind load on the turbine.

Abstract: A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.

Abstract: A system and method for converting, storing and distributing energy from renewable and non-renewable sources is provided, particularly a system to convert, store and distribute energy in the form of chemical energy in hydrogen (H2). A vertical-axis radial-flow turbine is also provided for the conversion of energy from renewable and non-renewable sources, such as solar energy, wave energy, and wind energy. Further provided herein is a multiple-column flow-control oscillating water column generator for the conversion of energy from wave and wind energy.

Abstract: A wind turbine that is mounted on a corner of a building and has a shaft that extends upward and outward from the corner, where the turbine blades are located, and the resulting rotation of the shaft is used for some power consumption purpose in our outside the building.

Abstract: A propeller fan includes a hub 1 and a plurality of blades 2, which are radially arranged on the outer circumference of the hub 1. A plurality of bent surface-shaped recesses 21 to 23 are formed on the positive pressure surface at a trailing edge 2b of each blade 2. The recesses 21 to 23 extend in the rotation direction of the fan and are arranged in a radial direction. Protrusions 24, 25 are each formed between adjacent pair of the recesses 21 to 23. The bent surfaces of the recesses 21 to 23 and the protrusions 24, 25 reduces air flow caused by centrifugal force. This allows the air flow on the positive pressure surface of the blade 2 to easily flow along the recesses 21 to 23. As a result, air flow does not concentrate on the outer periphery of the blade 2, which reduces the differences in the velocity and volume of air flow between the outer tip 2c of the blade 2 and the hub 1. Accordingly, the blade 2 functions as a whole.

Abstract: A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

Abstract: In a steam turbine having a cross-over duct for delivering steam discharged from an intermediate pressure turbine to low pressure turbines, the intermediate pressure turbine provides two outlets for discharging exhaust steam, the low pressure turbine provides two inlets, and the outlets and the inlets are arranged on the same straight line as viewed from a planar direction. One of the outlets and one of the inlets which are close to each other are connected through a cross-over duct, the other of the outlets and the other of the inlets which are far from each other are connected through another cross-over duct, and the cross-over ducts are arranged to be at two stages in the up-down direction.

Abstract: To reduce the size of a rotary machine and to provide a rotary machine in which it is possible to achieve an improvement in reliability and performance of the rotary machine.

Abstract: A blower comprising: a vane wheel including a pair of grooves, and blades extending in a radial direction of the vane wheel in each groove, and a casing including stationary flow paths facing to the grooves respectively so that the gas urged in the grooves is capable of flowing in a circumferential direction in the stationary flow paths, a guide flow path extending in the axial directions to fluidly communicate with both of the stationary flow paths to enable the gas to flow from one of the stationary flow paths to the other one of the stationary flow paths, an inlet port for introducing the gas into the one of the stationary flow paths facing to the one of the grooves and an outlet port for discharging the gas out of the other one of the stationary flow paths facing to the other one of the grooves.

Abstract: A closure device for a compressor having at least one access opening, wherein the closure device includes a plug portion disposeable at least partially within and configured to substantially obstruct the at least one access opening, a head portion having a shoulder surface extending generally radially outwardly with respect to the plug portion, wherein the head portion is generally disposeable against an inner surface of the compressor and configured to maintain the plug portion disposed within the at least one access opening during compressor operation, and a retainer member having a bracket engageable with an outer surface of the compressor and a threaded rod extending between the bracket and the plug portion, wherein the retainer member is configured to retain the plug portion disposed within the at least one access opening.

Abstract: A method and system for harvesting wind energy. The system may include a wind turbine disposed subjacent to a roof assembly of building. A plurality of conduits are adjacent to and extending below the wind turbine, wherein each of the plurality of conduits defines a first portion and a second portion, wherein the first portion defines a larger cross-sectional area than the second portion.

Abstract: A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal.

Abstract: A power converting device includes a main body having a heat producing part housed therein, a fan case having a cooling fan therein for cooling the heat producing part provided in the main body, and a housing portion in the main body which houses the fan case. The fan case and the housing portion are interconnected so that the fan case is pivotally attached to and detached from the housing portion.

Abstract: A machine for recovering power from a flow of compressed gas, for example, natural gas includes a turbo-expander having a turbo-expander wheel, and a generator having a rotor able to be driven by the turbo-expander wheel and a stator about the rotor. The turbo-expander and the generator are housed in a length of pipe. The turbo-expander wheel has an obverse side facing the generator. There is a flow passage for the flow of expanded gas that places the obverse side of the wheel in gas flow communication with an outer surface of the stator. This outer surface typically carries fins to facilitate cooling of the stator by expanded gas from the turbo-expander.

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: A nacelle for a wind turbine, the nacelle having a first height in its installed position and a second height in its transported position, the first height being higher than the second height, comprising a bottom part having a bottom face and two opposite side faces defining a space and a width of the bottom part and a top part. In the transported position, the top part extends inside the width or outside the width in order to cover at least part of the space. The invention also relates to a transportation kit and a transport method.

Abstract: This invention relates to increasing the use of an adjustable or flexible augmenter for increasing the power generation primarily used for utilizing wind energy. The adjustable augmenter is a wind enhancement structure with a plurality of flexible walls connected to each other with supporting horizontal elongated members. In the preferred embodiment, the invention is used with a plurality of smaller blades on a rotation means connected to a tower structure with a plurality of the rotation means and an inlet air flow regulation to achieve optimal power output. A preferred embodiment includes lightweight low cost structure of flexible wall to enhance an air flow into impact impellers connected to a rotation means creating a swept area with a height to diameter ratio of greater than four. A preferred embodiment includes wherein said impact impellers connected to a rotation means creating a swept area with a height to diameter ratio greater than ten.

Abstract: A heat dissipating device includes an outer frame, a first rotor, a base, a second rotor and a driving device. The first rotor comprises a shaft, a first hub and a plurality of first rotor blades disposed around the first hub. The base is disposed in the outer frame. The second rotor comprises a plurality of second rotor blades, coupled to the shaft of the first rotor and disposed next to the first rotor. The driving device is supported by the base for driving the first rotor and the second rotor.

Abstract: A fan housing includes a casing body, two air vents, an assembling portion, two supporting ribs and a side outlet. The air vents and assembling portion are formed in a base plate of the casing body. The assembling portion is surrounded by the air vents. The supporting ribs spaces out the air vents. A remaining portion of the base plate other than the air vents, the assembling portion and the supporting ribs being defined as a border that surrounds and adjoins the air vents, with each supporting rib linking the assembling portion and the border. A dividing line is defined in the base plate to divide the casing body into an output section close to the side outlet and a temporarily-staying section away from the side outlet by the dividing line, and each supporting rib is not completely within the output section. Consequently, turbulence in the output section is suppressed.

Abstract: A bladeless fan assembly for creating an air current includes a nozzle mounted on a base. The nozzle comprises an interior passage and a mouth for receiving the air flow from the interior passage and through which the air flow is emitted from the fan assembly. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle is detachable from the base, which is preferably sized to be accommodated within the opening of the nozzle for transportation.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: This actuator for an aircraft engine nacelle mobile structure (9) comprises a motor (1) intended to be mounted on a fixed part of the said nacelle, an endless screw (21) able to be turned by this motor (1), a slideway (5) intended to be connected to the said mobile structure (9) and comprising a nut (29) in mesh with the said endless screw, and a first ball end (15) allowing an angular offset between the axis of the said endless screw (21) and the said slideway (5). This actuator is notable in that it comprises a sleeve (19) able to accommodate the said screw (21) and extending with clearance inside the said slideway (5), the said nut (29) being mounted on that end of the said sleeve (19) that is closest to the said motor (1), and the said first ball end being interposed between the other end of the said sleeve (19) and the said slideway (5).

Abstract: A housing for a thermal turbomachine is provided. The housing includes an inner layer and an outer layer. The inner layer is subjected to greater thermal loading and the outer layer is subjected to less thermal loading, the inner layer being made of a more heat resistant material than the outer layer. Further, a method for producing a housing for a thermal turbomachine is provided.

Abstract: A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case.

Abstract: A fan assembly 1 for a gas turbine, the assembly 1 comprising: a fan surrounded by a fan casing 2; a resilient, flexible containment material 4 around the outside of the fan casing 2 for containing a detached fan blade which breaches the casing 2 during a fan blade off event, and a retaining cable arrangement for resisting separation of a first and second portion of the casing 10, 12 as a result of said breach, wherein the cable arrangement comprises: a continuous length of retaining cable 14 extending around the fan casing 2 on the outside of the containment material 4, the retaining cable 14 being slidably or rollably secured to each of the first and second portions 10, 12 at a plurality of positions around the fan casing 2 to form respective cable spans 14a, 14b between the casing portions 10, 12, there being sufficient overall slack in the cable 14 for accommodating radial flexing of the underlying containment material 4 upon impact of said detached fan blade.

Abstract: Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member.

Abstract: A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped.

Abstract: A method for repairing damaged bolt holes in a flange having a plurality of circumferentially spaced bolt holes therein, with each bolt hole defining a center axis and the flange defining an outer diameter edge. The method includes removing parent material of the flange in a first pattern, and metallurgically joining a replacement detail to the parent material of the flange a location where the parent material of the flange was removed in the first pattern. The first pattern is bounded by first, second, third and fourth points. The first point corresponds to the center axis of a first of the plurality of bolt holes, the second point corresponds to center axis of a second of the plurality of bolt holes, and the third and fourth points are defined at the outer diameter edge of the flange circumferentially spaced from each other.

Abstract: An apparatus and associated method is provided for injecting a processing fluid in a device that operably rotates a disc stack. A fluid injector has a nozzle defining an outlet sized to longitudinally span the disc stack to operably direct the processing fluid toward the disc stack. The nozzle also has a flow rate feature that operably directs a first flow rate of the processing fluid from the nozzle into a space adjacent a storage surface of a first disc of the disc stack and that directs a substantially different second flow rate of the processing fluid from the nozzle into another space adjacent a storage surface of a second disc of the disc stack.