Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: An exhaust diffuser for a turbine includes an inlet configured to receive exhaust gas from a last stage bucket of the turbine and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70. A method of diffusing exhaust of a turbine includes energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine.

Abstract: A bladeless fan includes a wind supply device and a first wind guide device disposed on the wind supply device and having a loop-shaped space. Airflow is created by the wind supply device, and enters the loop-shaped space. When the airflow exits the loop-shaped space through an air outlet, surrounding air is forced to flow through a flow guide channel in the first wind guide device to combine with the air flowing from the air outlet, so as to increase the amount and speed of the airflow.

Abstract: An automotive HVAC diffuser connects to a blower and a variable blower control (VBC) module having a plurality of cooling fins. An inlet receives air flow from the blower. An outlet is downstream from the inlet. An enclosed passageway is provided between the inlet and the outlet for forming a diffused air stream at the outlet. The enclosed passageway has a plurality of peripheral walls for guiding the air stream between the inlet and the outlet, including a curved outer peripheral wall corresponding to a region with a tendency for a high flow as a result of centrifugal effects. One of the peripheral walls includes a VBC receptacle formed as a depression into the peripheral wall having a substantially flat mounting surface and a first sloped side at an upstream end of the VBC receptacle to shape a portion of the diffused air stream.

Abstract: A fan assembly includes a mounting bracket, a fan, and a baffle. The mounting bracket includes two side plates bounding an outlet, and each side plate defines a through hole. An inner side bounding the through hole defines an arc-shaped cutout, communicating with the through hole. The baffle includes two pins rotatably received in the through holes of the side plates. A protrusion protrudes out from each pin, and is engaged in the corresponding cutout. When the fan operates, the baffle is pushed to rotate to open the outlet, to allow air from the fan to flow out through the outlet. When the fan ceases operation, the baffle rotates back under force of gravity to a position to cover the outlet, where the protrusion resists against one end of the cutout such that further rotation is prevented, to prevent air intake into the mounting bracket through the outlet.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly.

Abstract: A gas turbine according to the present invention includes: a strut which passes through an outer diffuser and an inner diffuser, and connects an exhaust chamber wall and a bearing housing; a strut cover which covers the strut along the extending direction of the strut; a partitioning wall which is arranged between the inside of the inner diffuser in the radial direction and the outside of the bearing housing in the radial direction, of which the upstream side portion is sealed between the bearing housing and the partitioning wall, of which the downstream side portion is sealed between the inner diffuser and the partitioning wall, and in which a strut through-hole through which the strut passes is formed; and a hole seal member which seals a gap between the strut through-hole and the strut.

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

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A two-stage high pressure turbine includes 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: Systems are provided that may be used to diffuse and deflect the flows of gas into a plurality of gas flows. A gas flow, for example, exhaust gas, may be diffused, that is, spread out by the diffuser. A flow deflector may be coupled to the diffuser so that the gas flow may result in a plurality of gas flows. By diffusing and allowing a plurality of gas flows, improved gas flows may be achieved.

Abstract: An electric blower includes a stator, a rotor, a bracket, rotary fan, air guide, a fan case covering air guide and rotary fan. Air guide includes a partition plate, a diffuser, a partition slope, and a guide vane. Diffuser vanes configure closed passages. Passage lengths of closed passages include a first passage length and a second passage length that is different from the first passage length.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: The total-to-static pressure ratio is increased across a Ram Air Turbine (RAT) by developing a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Lobe mixers in various locations improves mixing between the accelerated flow and the turbine exhaust flow, and the combined exhaust flow and the free-stream air surrounding the aerodynamic body.

Abstract: Tip shrouds on last stage buckets for condensing steam turbines may create significant blockage and form a vortex at the wall of the steam guide of the diffuser, causing the steam flow to separate from the wall of the steam guide. Vortex formation reduces the effective flow area for the remaining fluid to diffuse, causing poor recovery. An inward radial depression is provided of a predetermined depth and distance along an outer steam guide, which redirects the tip leakage flows slightly downward, reducing a shroud blockage effect. This deflection assists the main flow in rejoining the steam guide, thereby making the diffuser more effective.

Abstract: A method for assembling an exhaust hood for a turbine is provided. The method includes providing a bearing cone that substantially circumscribes a rotor of the turbine; and positioning a guide radially outward from the bearing cone. The guide and the bearing cone are configured to channel fluid from the turbine. The method also includes extending a guide cap from the guide. The guide cap is oriented to facilitate preventing the generation of fluid vortexes within the exhaust hood.

Abstract: The present teachings relate to an air feed device with at least one impeller; with at least one housing that at least partially surrounds the impeller, with at least one intake opening for inward suction of air into an operating space of the impeller, with at least one opening to blow out air from the operating space of impeller. Provision is made that the air feed device has at least one additional through-passage opening for air.

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: A diffuser for an axial flow machine has a transition from a ring channel having a first cross sectional area into an outlet space with a second, larger cross sectional area along a machine axis of the axial flow machine. The transition includes a plurality of steps.

Abstract: A vacuum pump (1) includes: a rotor (30) provided with a rotor-side discharge function unit (32); a motor (36) that drives the rotor (30) to rotate with respect to a stator-side discharge function unit (22); and a cylindrical pump casing (2) made of a magnetic material, in which the rotor (30) and the stator-side discharge function unit (22) are disposed.

Abstract: In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure variations caused by the stagnation effect of the installations and reacting on the fan are reduced, enabling the fan to be operated with more efficiency and stability and finally the losses of the overall system and the fuel consumption to be reduced. The cross-sectional enlargement is accomplished by modifying the course of the wall in a limited area, actually by gradually enlarging the flow cross-section in the bypass duct in the axial and in the circumferential direction, with this enlargement being confined to the area around the leading edge of the support struts and/or the aerodynamic fairings.

Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly defined about an axis and a core engine positioned radially inward of the nacelle assembly and having a core passage and at least one core auxiliary duct passage. The at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from the core engine and an outlet for discharging the portion of the core airflow. At least one of the inlet and the outlet are selectively translatable to divert the portion of the core airflow into the at least one core auxiliary duct passage and a mixer disposed between the nacelle assembly and the core engine.

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base includes an outer casing, a silencing member housed within the outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller about an axis to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly. The silencing member is located beneath the air inlet of the impeller housing and is spaced from the air inlet along said axis by a distance in the range from 5 to 60 mm.

Abstract: A gas turbine exhaust strut installed in an exhaust case of a gas turbine is disclosed which includes a trailing portion configured with an inner surface for mounting to an inner annular member of the exhaust case and an outer surface for mounting to an outer annular member of the exhaust case, a block attached to the trailing portion, an angled piece attached to the block and configured with a surface on a pressure side of the strut angled with respect to a surface of the trailing portion on the pressure side of the strut, and a transition piece attached to the block and configured with a surface on the pressure side of the strut for smoothing the transition between the height of the block on the pressure side of the strut and the height of the trailing portion on the pressure side of the strut. A method of refurbishing an exhaust strut installed in an exhaust case of gas turbine while retaining at least a portion of the strut in the exhaust case is also disclosed.

Abstract: An impulse wind machine comprises the following: A funnel configured to capture air from the wind. A turbine housing configured to direct the air to the center (eye) of the housing where the air passes through directional vanes. A rotor configured to rotate within the eye of the turbine housing and configured with impulse blades along the longitudinal periphery. Air from the directional vanes impinges the impulse blades to cause rotor rotation. An exhaust deflector configured inside the cavity of the rotor to deflect exhaust air from the impulse blades axially out the ends of the rotor. Spokes on the rotor configured to provide a fan action during rotor rotation aiding removal of the exhaust air. A generator and a gearbox driven by a shaft connected to the rotor for generating electrical power.

Abstract: A diffuser pipe (38) of a compressor diffuser assembly (28) for gas turbine engines defines a depressed local area (58) in the pipe wall of an upstream section of the diffuser pipe (38). The depressed local area (58) is bent into the diffuser pipe (38) to reduce the accumulation of fluid boundary layer and improve stall margin of the diffuser pipe (38).

Abstract: An asymmetric butterfly plate for a steam turbine exhaust hood includes a non-symmetrical curvilinear profile having a first section that extends to a second section through a vertex. The first section has a first curvilinear profile and the second section has a second curvilinear profile that is distinct from the first curvilinear profile.

Abstract: A pedestal for a fan assembly includes a telescopic duct for conveying an air flow to an outlet of the fan assembly. The duct includes an outer tubular member having a first stop member, an inner tubular member located at least partially within and slidable relative to the outer tubular member, the inner tubular member having a second stop member for engaging the first stop member to inhibit withdrawal of the inner tubular member from the outer tubular member, and a mainspring rotatably mounted on the second stop member, the mainspring having a free end retained by the first stop member.

Abstract: A diffuser apparatus includes a diffuser communicating radially outwardly with an exit of an impellor. The apparatus includes a housing with a plate that is rotatable about a rotational axis and forms a hub side wall. A side surface of the plate has a vane having one circumferential end fixed to the plate; the other end is movable in the direction of the axis. The housing includes an inclination path with one end opened to the hub side wall to bendably guide the vane so that the other end of the vane moves in the circumferential direction upon rotation of the plate and moves in the direction of the axis to a projected position to project into the diffuser. An actuator rotates the plate to drive the vane between the projected position and a retracted position where the other end is retracted into the hub side wall.

Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.

Abstract: A fan assembly for creating an air current includes an air inlet, an air outlet, an impeller and a motor for rotating the impeller to create an air flow passing from the air inlet to the air outlet. The air outlet includes an interior passage for receiving the air flow and a mouth for emitting the air flow. The air outlet defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The motor has a rotor which, in use, is capable of rotating at a speed of at least 5,000 rpm.

Abstract: A submersible pump stage comprises an impeller comprising a first front top disc and a first rear top disc, first blades located between the front and the rear top discs, a bushing and a diffuser comprising a second front top disc and a second rear top disc, second blades located between the second front and second rear top discs. The second rear top disc has through holes passing in end surfaces and located circumferentially. A number of the through holes is selected at least equal to a number of interblade channels. The holes are made so as to provide an overflow of a liquid from a front pocket of this stage of the submersible pump into each interblade channel of a preceding stage diffuser.

Abstract: A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling region formed from endwall cooling channels having a higher density of cooling channels than other areas in order to cool the material forming the intersection between the trailing edge of the airfoil and the endwall to prevent premature cracking. The increased density of cooling channels in the endwall at the trailing edge forms a heat sink that draws heat from the airfoil, thereby lowering the temperature of the airfoil and increasing the useful life of the airfoil.

Abstract: A structural composite fan exit guide vane assembly uses single component monolithic structural guide vane segments to provide airflow correction and structural support in a gas turbine engine.

Abstract: A turbine housing of an exhaust gas turbocharger includes an outer casing and a rotor casing which is arranged in the outer casing and includes a tubular neck for engagement in an exhaust pipe to conduct exhaust gas from the neck in a direction of an exhaust flange. The exhaust pipe is hereby coupled to the rotor casing for relative movement there between. A sealing ring is arranged between the neck and the exhaust pipe, wherein the neck has one end provided with at least one outwardly directed projection defined by an outer diameter which is greater than an inner diameter of the sealing ring. Fabrication of the turbine housing is realized by pushing the sealing ring over the neck, and inserting an expanding mandrel into the neck to widen the neck.

Abstract: Turbine systems for extracting energy from water traveling relative to the turbine system can include a rotor assembly for extracting the energy, a turbine shroud having a turbine shroud inner volume within which at least a portion of the rotor assembly is disposed, and an ejector shroud disposed adjacent to the turbine shroud. The turbine shroud and the ejector shroud can each have a terminus comprising a plurality of turbine shroud mixer elements or ejector shroud mixer elements, respectively. One or more of the mixer elements and ejector shrouds comprise a mixer/ejector pump which increases the energy extraction potential of the turbine system. One or more of the turbine shroud mixer elements, ejector shroud mixer elements, and ejector shroud and turbine shroud inlets can be asymmetric along a plane passing through the axis of rotation of the rotor assembly.

Abstract: The Vortex Hydro Turbine takes water through an inlet from the current in which it is submerged. The water inlet reduces the cross-sectional area for the water that flows into the vortex chamber and thus increases the velocity of the water into a specially designed cylindrical chamber. The top of the chamber is specifically left open allowing the water now traveling at an increased velocity to disperse toward outlet as it rotates around the chamber, and then reintegrate into the existing environmental regime. This expansion creates a low pressure area in the center of the vortex chamber that is applied to the back side of a turbine blade system either directly or through a connecting tube depending on configuration.

Abstract: A technique is provided for improving the efficiency of a centrifugal pump. The centrifugal pump comprises diffusers that optimize the area schedule through the diffuser to diffuse the total fluid velocity and recover dynamic head while minimizing flow separation. Each diffuser comprises an improved transition from the diffuser blade into the diffuser discharge duct to remove abrupt changes in area and to reduce fluid separation. The impellers also can be constructed with impeller transitions able to reduce fluid separation and improve the efficiency of the pump.

Abstract: A nozzle for a turbine includes a duct member having a substantially uniform wall thickness. Nozzles made of different materials can be used.

Abstract: A blower includes an electric motor having a shaft, a housing having an inlet and outlet between which is defined a gas flow path, the outlet structured to direct gas exiting the blower in an axial first direction, a first impeller attached to the shaft and adapted to accelerate air tangentially and direct it radially outward, a stationary portion, and a shield. The stationary portion includes a first stator vane structure defining a plurality of stator vane leading edges and a stator vane outer radial edge. The first stator vane structure is arranged to direct gas flow along a curved path that directs flow at an inner end thereof in a radially inward direction. The shield has an outer edge extending radially beyond the outer radial edge of the first stator vane structure and is adapted to isolate the stator vane leading edges from an impeller blade pressure pulse.

Abstract: A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.

Abstract: Humidifying apparatus includes a humidifier for emitting moist air into an external environment, and a fan assembly for generating an air current within the external environment for conveying the emitted moist air away from the humidifier. The fan assembly includes a device for creating an air flow and a nozzle comprising an interior passage for receiving the air flow and a mouth for emitting the air flow. The humidifier is located behind nozzle, the nozzle extending about and defining an opening through which both air from outside the nozzle and the moist air emitted from the humidifier are drawn by the air flow emitted from the mouth.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly.

Abstract: An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold.

Abstract: The present disclosure relates to a tower fan having a base and a column coupled to the base. A blower is positioned within the column. The blower has an inlet and an outlet, and the outlet twists about an exterior of the column along a longitudinal axis of the column.

Abstract: A cooling fan includes an impeller which comprises a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip. In addition, each blade includes a camber of between about 60° and 90° at the blade hub, between about 15° and 40° at the blade midspan and between about 15° and 40° at the blade tip.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: The turbine outlet heated diffuser may include a cavity positioned immediately downstream of an air cycle machine turbine. The turbine outlet heated diffuser may be designed to prevent or reduce ice formation at the turbine outlet by heating the diffuser wall. The cavity may receive a heated flow from an air cycle machine compressor discharge and provide a cavity outlet flow to a turbine inlet plenum. The design of the heated diffuser is such to minimize the cycle performance impact that results from the addition of an air cycle machine icing protection feature.