Abstract: A micro-air motor comprises a collector rotatably mounted in a casing for the compressed air supply and discharge to or from the rotor. By twisting the collector as far the end positions a direction of rotation reversal as well as continuous speed regulation is possible. In a neutral position of the collector the rotor can be additionally stopped and locked.

Abstract: A telescopic chimney and methods are disclosed for generation of mechanical energy using air routed through a turbine. Truncated cones stored nested together telescope to interlock when extended end to end to form a conical shape that diverges upwardly. An air output deflector at the exit of the chimney drives the exiting airflow downwards and is optionally divided into six equal radial spans so that airflow can be varied through each by a computer-controlled shutter to compensate for wind forces. An axial cable raises and lowers truncated cones. A method of deploying the chimney includes steps of closing the shutters; filling the truncated cones with heated air; controlling the rise of the truncated with the cable; and, opening the shutters. A method of collapsing the chimney includes the steps of pulling the cable to exert downward force on a truncated cone.

Abstract: A system generating electrical power from wind includes a cowling to capture wind and directs it into a tubular housing. At least one fixed helical vane can be integrated into the inner surfaces of the tubular housing in a spiral, adapted to further direct the captured wind into a spiraled air flow and focus the wind directly onto electrical generator fan blades located near an exhaust of the system. A generator cone can be mounted at the front of the generator or fan blades facing air passing through the tubular housing. As air passes over the generator cone it can experience compression between the generator cone and housing resulting in increased pressure and velocity of the air, thereby increasing rotational speed of the generator blades and generator as the compressed air passes through the blades and exits the system's exhaust. The system can be used for fixed or mobile applications.

Abstract: A two-stage high pressure turbine comprises a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.

Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.

Abstract: A method of repairing a nozzle segment is provided. The nozzle segment includes at least one airfoil extending between an inner band and an outer band, and the airfoil includes a first sidewall and an opposing second sidewall that are joined together at a leading edge and at an axially-spaced trailing edge. The method includes identifying a damaged portion of the airfoil, repairing the damaged portion of the airfoil by at least one of welding weld filler in the area of the damaged portion of the airfoil, and brazing preform in the area of the damaged portion of the airfoil, and blending at least one of the weld filler and the preform to remove excess material to facilitate finishing an outer surface of the airfoil.

Abstract: An exemplary port (180, 180?) includes a first port opening (182, 182?) positioned at a location downstream from a compressor wheel (140), a second port opening (184, 184?) positioned at a location adjacent to a blade (144) of the compressor wheel (140), and a third port opening (186, 186?) positioned at a location upstream from the compressor wheel (140) wherein the first port opening and the third port opening define a first flow path and wherein a second flow path extending from the second port opening meets the first flow path at a confluence (188, 188?). The first flow path optionally includes a venturi section, for example, wherein the confluence coincides at least in part with the venturi section. Other exemplary ports, compressor shrouds, systems and methods are also disclosed.

Abstract: A blade for a turbine engine is described, having a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection region, to prevent local concentration of tension, such that the above borders directly on the second component piece and forms therewith a connection angle greater than 70 degrees.

Abstract: A humidifier (1) includes a gaseous flow-generating unit interacting with a unit for producing fluid droplets in such a way that a mist is formed. According to the invention, the gaseous flow-generating unit includes a centrifugal fan (2) which is provided with an input (5) oriented along the axis of rotation of the fan (2) and a radial output (6) for generating a radial droplet-transporting flow.

Abstract: A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum.

Abstract: The present invention provides an improved fan frame with a diversion structure. A cooling fan includes a rotor, and fan blades spaced around the rotor at intervals. The fan frame positions the rotor and defines a diversion loop, which corresponds to the air outlet direction when fan blades are turning and has an expanding diversion surface. The fan frame has a diversion surface with diversion ribs spaced at intervals, the placement of the diversion ribs being in a vortex pattern without passing through the hypothetical point of the rotor center. The airflow generated by turning fan blades is guided by the diversion ribs and converted to outlet airflow in axial direction corresponding to the rotor, effectively reducing impact and friction of the gyrate airflow generated by fan blades against the frame diversion surface, lowering the noise level, making air exhaustion smoother, and improving the cooling efficiency of fan.

Abstract: A centrifugal blower capable of preventing generation of a swirled air stream in a space between the inner surface of a casing and a side end of a centrifugal fan, and an air conditioner having the same. The centrifugal blower includes a casing having an air inlet, an air outlet, and a bell-mouth located near the air inlet, a centrifugal fan installed in the casing, and a stream-cutoff member provided at an inner surface of the casing around the bell-mouth to prevent an air stream from being swirled in a space between the inner surface of the casing and a side end of the centrifugal fan.

Abstract: A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages.

Abstract: Provided is an axial fan apparatus including a housing and an axial-flow impeller. The axial-flow impeller is capable of rotating inside the housing and includes a plurality of axial-flow wings each having a negative pressure generation surface for generating a negative pressure, and an auxiliary vane standing on the negative pressure generation surface at an end portion of each of the plurality of axial-flow wings.

Abstract: A cooling fan comprises a fan housing, a motor which is positioned within the fan housing, a plurality of electronics components which are associated with the motor, and at least one strut which extends radially between the motor and the fan housing, and on which the electrical components are mounted.

Abstract: There have been past proposals for air vehicles employing the Coanda effect. In these proposals, a jet of fluid, usually air, is made to flow radially outwardly over a dome-shaped canopy to create lift. A cross-section through the canopy is curved to follow a segment of a circle or it may have a radius of curvature that increases in the direction of flow. In the invention, the radius (r) of the canopy curve decreases towards the downstream direction (x) in a way that is related to the decrease in the width of the jet as it flows over the surface. This means that the radius of curvature decreases (instead of increasing) towards the downstream direction with the rate of decrease being progressively less rapid towards the downstream direction.

Abstract: A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.

Abstract: An outer shape of a section in the longitudinal direction at a leading edge of the strut is an aerofoil whose thickness is gradually increased along a flow direction of the combustion gas to prevent reduction of turbine efficiency caused by a shock wave generated at the strut of the exhaust diffuser.

Abstract: A system for providing low cost electric power without consumption of limited natural resources, pollution, or greenhouse gas emission, and is independent of wind conditions. Additionally, the system of the present invention includes a venturi-like collar positioned at the top of one or more stacks increasing air flow.

Abstract: A technology for widening the operating range of a high-pressure ratio centrifugal compressor including a vaned diffuser is provided. The solidity of each vane in the vaned diffuser is set to the optimum value at which the region, in which burbles do not occur when the air flows into the diffuser, is wider than the region, in which burbles may occur when the air flows into the diffuser. In addition, the solidity is set in such a manner that the straight line, which extends outward from the inner peripheral edge of the vane at a right angle with respect to the chord of the vane, does not cross the adjacent vane. In this way, formation of a throat between the vanes is suppressed.

Abstract: A method for fabricating an outlet guide vane includes the steps of fabricating a structural spar from a first material, fabricating a fairing from a second material, and installing the fairing onto the spar so as to at least partially surround the spar and form an airfoil. An outlet guide vane includes an airfoil including a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar. A gas turbine engine assembly includes a core gas turbine engine, a fan assembly including a plurality of fan blades coupled to the core gas turbine engine, and a plurality of outlet guide vanes coupled downstream from the fan blades, at least one of the outlet guide vanes including an airfoil having a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar.

Abstract: A blower/vacuum and an impeller for use with generating air flow in a blower/vacuum. The impeller may include a hub for mounting the impeller on a rotatable output shaft of a motor of the blower/vacuum. The impeller may further include a plurality of air-flow generating blades that define a particular range of inlet and outlet angles. Additional features of the impeller may include a plurality of shortened member that facilitate mulching of air-entrained debris.

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface.

Abstract: A fluid pump of the present invention comprises a rotating chamber, a rotor which rotates about a rotating axis within the rotating chamber and includes a hub and a vane protruding radially outward from the hub; and a pair of blocking walls which cooperate with the vane and linearly move upon rotation of the rotor. A suction port for suction of a fluid and a discharge port for discharge of the fluid are provided at both positions adjacent to the pair of the blocking walls which are interposed between the ports.

Abstract: A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.

Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.

Abstract: A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed.

Abstract: A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.

Abstract: A gas turbine combustion chamber includes an annular combustion chamber (3) confined by an outer (1) and an inner combustion chamber wall (2) and is provided with several fuel injection nozzles (4). Air deflectors (6) are arranged in a front-side area of the annular combustion chamber (3) over the entire combustion chamber annulus (5) concentrically around a combustion chamber axis (12) and fuel injection nozzles (4) are distributed essentially uniformly over the combustion chamber annulus (5).

Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.

Abstract: A replacement fan exit guide vane assembly for installation between an inner case and an outer case of a gas turbine engine includes an airfoil structure having an outer end and an inner end, a wedge structure connected to the outer end of the airfoil structure, a base plate positioned between the outer end of the airfoil structure and the outer case, a conformable material, and a slip collar having an opening therethrough and a recess formed along the opening. The airfoil structure extends through the opening, and the recess accepts the wedge structure to create an interference fit between the slip collar and the base plate. The conformable material is disposed along the opening and the recess in the slip collar, and also along the baseplate, in order to provide dampening relative to the airfoil structure and the wedge structure.

Abstract: A two-stage high pressure turbine includes a first stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A low profile pump inlet for an implantable blood pump is disclosed. The low profile pump inlet has an inflow diffuser for attachment to a conduit bearing an inflow of a fluid such as blood and an outflow orifice in fluid connection with the diffuser. The outflow orifice is configured to direct the fluid from the diffuser into a pump such as an implantable blood pump. The low profile pump inlet helps to suppress the effects of upstream pipe bends on the blood traveling through the inlet. The inlet thus provides a flow having a substantially uniform velocity profile into the blood pump.

Abstract: An integrated duct, baffle and knife edge seal arrangement employing the radially inner distal edge of the baffle for sealing the radially inner stator/rotor interface of an inter-stage cavity.

Abstract: System for ventilating a combustion chamber wall in a turbomachine comprising a diffuser (12) mounted at the inlet of the combustion chamber (14) and comprising an annular end-piece (28) that extends downstream to means (42) for injecting ventilation air, an annular convecting metal sheet (100) being arranged radially between the combustion chamber and the end-piece of the diffuser in order to delimit, with an internal wall of the chamber, an annular stream (90) for the flow of air that is stable and without separation supplying holes in the chamber and the injection means.

Abstract: A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each include at least one open passage. The airfoil vane extends between and is coupled to the endwalls. The vane further includes a cavity, a leading edge, a trailing edge, and an airfoil vane external surface. The cavity includes an airfoil vane internal surface and a plurality of turbulators. The cavity and the open passages are in flow communication such that an airfoil cooling air stream flow is facilitated. The sub-system also includes at least one diffuser in flow communication with a compressor assembly and the segment. The diffuser includes at least one diffuser wall and cavity. The diffuser wall extends from the compressor assembly to the segment such that a channeling of the airfoil cooling air stream to the segment is facilitated.

Abstract: An integrated centrifugal blower wheel for a heating, ventilation and air conditioning (HVAC) blower unit includes a first blade support, a second blade support, and a plurality of S-shaped blades disposed between the first and second blade supports, wherein each of the S-shaped blades has a trailing edge bent in a forward direction with respect to a defined direction of rotation of the wheel.

Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

Abstract: In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.

Abstract: The axial fan for a computer comprises a rotatable fan blade unit and a motor unit. The fan blade unit comprises a fan head and a plurality of fan blades arranged radially thereto. The motor unit is held by supports passing through the airflow. The supports have a distance of at least 7.5 mm from the fan blades measured in axial direction. Due to this distance being larger in comparison to known solutions the fan produces less disturbing noise.

Abstract: A blower (1) has a housing (10) to which a blower pipe (2) may be removably connected. An internal combustion engine located within the housing (10) drives a blower wheel. The blower wheel, in turn, generates an air flow (11) within the blower pipe. To reduce the exhaust gases and the fuel consumption during idle operation of the combustion engine, a reduction device (12, 22), located in the blower pipe downstream of the blower wheel reduces the clear cross section of flow during idle operation of the engine.

Abstract: A casing for a heat exchange system defines a blower compartment (18), an evaporator compartment (20), and a diffuser (22). The diffuser (22) defines an exit (28) and an entry area in a cutoff plane (30). A vane wall (38) curves inwardly from the diffuser (22) and includes a plurality of parallel vanes (46), (48), (50), and (52). The plurality of vanes (46), (48), (50), and (52) include a first vane (46) and a second vane (48).

Abstract: A method of tuning a compressor stator blade having a base portion and an airfoil portion to achieve a desired natural frequency, includes a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency. A frequency-tuned compressor stator blade includes an airfoil portion and a base portion, the base portion having a substantially solid rectangular shape; and a groove cut across a width dimension of the base portion, the groove having dimensions selected to obtain a predetermined natural frequency for the airfoil portion.

Abstract: An impingement baffle includes a perforate plate having a pattern of impingement holes. An imperforate deflector is spaced from the plate and is smaller than the plate for deflecting inlet air around the deflector to the holes. The baffle is disposed between a turbine shroud and supporting hanger, and the deflector is disposed between the hanger and the baffle.

Abstract: A heat-dissipating fan module of an electronic apparatus is disclosed. The heat-dissipating fan module includes a casing having an opening, the opening having a guiding device along an edge thereof, and a heat-dissipating fan fixed to one side of the casing and correspondingly disposed on the opening.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A turbine blade or vane includes an inner contour profile which is matched to the contour profile of the outer transition region, so that a substantially uniform blade or vane wall thickness is achieved.

Abstract: The stator vane is provided with a leading edge which is cut into a different depth in dependence on a span-wise position so that a blade inlet angle may vary along a span-wise direction according to a prescribed pattern. By thus optimizing the depth of the cut along the leading edge of the stator vane, the leading edge blade inlet angle can be optimized along the entire length of the stator vane even if the stator vane consists of a two-dimensional aerofoil, and the vane is provided with a substantially conformal cross section in parts which are not affected by the cut in the leading edge. Thereby, the efficiency of the turbine can be optimized while minimizing the cost.

Abstract: The fan has a volute inlet. Designing the shape of inlet to improve the heat dissipation of the fan. The fan has a volute inlet having a reference point on the housing with respect to an outlet. The blades are partially covered by the inlet from the reference point wherein an area of the blades covered by the inlet is from a maximum to a minimum gradually in a closed loop. As a result, the set up current of air can reach a maximum prior to output from the outlet, thereby increasing the heat dissipation capability of the fan.