Abstract: A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct having a substantially circular shape and surrounding the engine core, and a plurality of coupling struts, each coupling strut extending only in a substantially vertical direction relative to the direction of gravity when the engine core is at a rest position with zero pitch and zero roll, each of the plurality of coupling struts coupling the engine core to the duct.

Abstract: A fan comprises a fan housing which includes a fan inlet, a motor which is connected to the fan housing, and an impeller which is removably connected to the motor. The impeller includes an impeller hub, a number of impeller blades which extend radially outwardly from the impeller hub, an impeller leading edge, an impeller trailing edge and an impeller tip. The fan housing includes an inlet shroud which is positioned over the impeller. The inlet shroud comprises an upstream end portion within which the fan inlet is formed and a downstream end portion which is removably connected to a separate portion of the fan housing. The inlet shroud further includes a first section which extends axially from the upstream end portion to approximately the impeller leading edge, a second section which extends axially from the first section to approximately the impeller trailing edge, and a third section which extends axially from the second section to approximately the downstream end portion.

Abstract: An axial flow fan includes: an impeller, a hub of which is attached to a rotation shaft of a rotation driving device; and a venturi casing that surrounds an outer circumference in a radial direction of the impeller and includes a suction port and a discharge port facing each other in an axial direction of the rotation shaft. A positive pressure surface of a plurality of blades integrally attached to the hub includes a plurality of step portions that is curved so as to comply with a curved shape of a front edge portion in a rotation direction of the blades.

Abstract: An axial flow fan assembly includes a plurality of fan blades surrounded by a shroud. The shroud includes an annular first wall which extends radially outwardly, an annular second wall which extends axially and radially outwardly, and an annular third wall which joins the first wall to the second wall. The third wall has a curved cross sectional shape, and has a minimum diameter part which is positioned approximately half-way between the upstream and downstream edges of the fan blades. There is a desired relationship between the radius of curvature of the third wall and the diameter of the fan. There is a desired relationship between the height of the first wall and the diameter of the fan. The fan blades have an upstream edge which is upstream with respect to the first wall.

Abstract: A columnar air moving device can comprise separately formed modular stator vanes in a stator vane assembly. The stator vanes can be arranged in a radial pattern, and can direct air in an axial direction. The modular stator vanes, as well as other components of the stator vane assembly, can be replaced, adjusted, and/or removed from the columnar air moving device.

Abstract: A turbine that allows for the conversion of the kinetic energy of waterway to mechanical power for use in an energy accepting apparatus is described. The turbine has complimentary components that improve the power efficiency of the turbine. The turbine may include a blade shroud and a plurality of blades that are connected to the blade shroud. On the external surface of the blade shroud, a drive mechanism and/or a brake mechanism may be disposed. An inlet nozzle and outlet diffuser may be used in combination with the turbine. The turbine may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: Various embodiments include an alignment pin for a turbomachine. In some embodiments, the alignment pin includes a hollowed head section for engaging a diaphragm slot in the turbomachine. In these embodiments, the alignment pin further includes an expandable sleeve section connected with the hollowed head, the expandable sleeve section for engaging a casing slot in the turbomachine.

Abstract: A mounting device for a fan includes a first mounting frame and a second mounting frame adjustably mounted to the first mounting frame according to the height of a fan, to sandwich the fan between the first and second mounting frames.

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

Abstract: The present invention is applicable to the technical field of heat-radiation structures and discloses a flow-guiding apparatus and an electronic device including the flow-guiding apparatus. The flow-guiding apparatus includes a support and flow-guiding members for guiding an air flow generated by an axial fan to a directed area, where the flow-guiding members are connected to the support, at least two flow-guiding members are arranged and are located on both sides of a hub of the axial fan or around the hub of the axial fan, and the flow-guiding members tilt toward the hub of the axial fan along an air-blowing direction of the axial fan. The electronic device includes a chassis, where the chassis is provided with an air vent, an axial fan is arranged at the air vent, and an air outlet of the axial fan is arranged with a flow-guiding apparatus mentioned above.

Abstract: An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body.

Abstract: A nozzle for a fan assembly includes an air inlet, an air outlet, an interior passage for conveying air from the air inlet to the air outlet, an annular inner wall, and an outer wall extending about the inner wall. The interior passage is located between the inner wall and the outer wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. A flow control port is located downstream from the air outlet. A flow control chamber is provided for conveying air to the flow control port. A control mechanism selectively inhibits a flow of air through the flow control port to deflect an air flow emitted from the air outlet.

Abstract: In a hydroelectric turbine having a rotor disposed within a housing, the rotor having an annular outer rim received by a channel in the housing, the improvement comprising providing at least one debris release chute in said housing such that debris captured between the rotor and the housing is released through the debris release chute.

Abstract: A fan module including two brackets, two holders and a fan is provided. Each bracket has a first assembling portion formed thereon. The holders are mounted to the brackets and located between the two brackets. Each of the holders has two second assembling portions, and one end of each of the second assembling portions being connected with the first assembling portions correspondingly. The fan is assembled between the holders.

Abstract: A radial upblast exhaust apparatus includes a fan housing having a fan inlet to receive air to be exhausted and a fan outlet to expel air to be exhausted. An upper housing is positioned immediately above the fan housing. It includes a first wall section and a second wall section each shaped as a partial conical section being concaved toward each other. The upper housing forms an air outlet nozzle. A mechanism changes the outlet area of the outlet nozzle in order to provide a variable area outlet for the fan.

Abstract: A turbine includes a rotor and a casing that circumferentially surrounds at least a portion of the rotor. The rotor and the casing at least partially define a gas path through the turbine. A last stage of rotating blades is circumferentially arranged around the rotor and includes a downstream swept portion radially outward from the rotor. A method for reducing shock losses in a turbine includes removing a last stage of rotating blades circumferentially arranged around a rotor and replacing the last stage of rotating blades with rotating blades having a downstream swept portion radially outward from the rotor.

Abstract: A containment assembly for a turbo fan engine, has a casing arranged in use around a rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface between the casing and blades of a rotatable fan. The liner element includes a body portion mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct. The wall portion and the body portion being attached and defining a containment cavity therebetween for containment of a detached fan blade fragment in use, wherein the wall portion has a moveable portion movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity.

Abstract: Implementations of an enhanced axial air mover system address various issues such as drying performance, transportability, storage, use, and assembly. Some implementations include ergonomic positioning of a carrying handle relative to positioning of a fan-assembly to make the system easier to carry. Enclosures with variable diameter profiles increase air flow performance. A floor edge allows for flush positioning of the air mover's outlet to improve flow of air. Various supports and engagement members allow for horizontal and/or vertical engagement of a plurality of the air movers for storage or increased air moving capacity for a given application. An alignment guide assists with positioning of the air mover with respect to a room wall to enhance air flow within the room. A cord retaining system provides an enhanced approach for securing the air mover's electrical cord. Grill guards have slotted ends to assist with assembly of the air mover.

Abstract: A drying fan has a shroud with a shape selected to improve fan efficiency by designated fluid dynamics of air flow through the fan.

Abstract: There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet engine includes a nacelle. The nacelle includes a forward extension proximate the fan and extending forward therefrom. The forward extension is funnel shaped to impart radial momentum to intake air during operation. The nacelle includes a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. The vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. The vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan.

Abstract: A turbine section of a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; and an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine. The inter-turbine duct has a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area. The first station is upstream of the second station and the second station is upstream of the third station, and the second meridional area is less than or equal to the first meridional area.

Abstract: A cooling apparatus for a motor vehicle with an internal combustion engine is provided that includes at least one heat exchanger through which air can pass, at least one axial fan that is located behind the at least one heat exchanger in a direction of air flow and has a circumferential ring with which ring is associated a stationary baffle ring, and a fan shroud adjoining the at least one heat exchanger. At least one motion compensating element with a sealing function is provided between the baffle ring and the at least one fan shroud.

Abstract: A fluid flow machine has a main flow path in at least one stage, with a rotor arrangement and a stator arrangement, resulting in an increased rotor-stator constriction ratio QRS, which satisfies the following equation: [0.2+(KT?0.45)0.1]<QRS, with QRS being defined to the following formula: QRS=KR/KS with KT being the total stage constriction, and with QRS and KT being determined as follows: QRS=KR/KS with KR=ARI/ARA and KS=ASI/ASA KT=ARI/ASA with ARI, ARA, ASI and ASA being calculated as follows: ARI=?(R22?R12) ARA=?(R42?R32) ASI=?(R62?R52) ASA=?(R82?R72).

Abstract: A system includes a rotor assembly with a first rotor component having a first set of bushing receptacles and a first set of bolt holes arranged about a first rotational axis of the first rotor component. The rotor assembly also includes a second rotor component having a second set of bushing receptacles and a second set of bolt holes arranged about a second rotational axis of the second rotor component. The rotor assembly includes a first set of bushings disposed in the first and second sets of bushing receptacles in a first installed configuration, wherein the first installed configuration of the first set of bushings is configured to align the first and second rotational axes with one another, and the first installed configuration of the first set of bushings is configured to bear at least a first portion of a torque during rotation of the rotor assembly.

Abstract: A method of forming a composite component in which the component comprises a series of sub-layers and in which the sub-layers are offset with respect to one or all of the other sub-layers forming the composite component.

Abstract: The invention relates to a locking device (13) that includes at least one locking system (16), intended to be placed on a first moving element (11), and a retaining member (17), intended to be placed on a second moving element (12), the locking system (16) having a first hook (18) designed to engage with the retaining member so as to lock the locking device (13). The locking system (16) includes at least a second hook (19) set back from the first hook (18) so as to engage with the retaining member in the event of the first hook (18) breaking.

Abstract: Gas turbine engine frames are disclosed. An example gas turbine engine frame may include a generally annular outer casing disposed coaxially about a hub; a plurality of circumferentially spaced apart struts joined to the hub and the outer casing, individual struts extending radially outwardly from the hub to the outer casing; and a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts. The stiffening rail may extend radially inward beyond the inner surface of the outer casing between the struts.

Abstract: The nacelle (1) comprises an air intake (5) upstream of the turbojet engine (2), a middle section (6) an internal casing (6a) of which is intended to surround a fan (3) of the turbojet engine (2), and a downstream section (7) comprising an external structure (7a)which is rigidly connected to a downstream part of the casing (6a) of the fan (3) so as to support the turbojet engine (2) and has means of attachment to a strut (12) intended to be connected to a fixed structure (13) of an aeroplane.

Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.

Abstract: An assembly includes a fan and a heat sink for detachably fixing the fan. The fan includes a pair of first and a pair of second sidewalls, with two pair of rims respectively extending from the first and second sidewalls. Ends of the rims of the first sidewalls, which are directed toward and are adjacent to a same one of the second sidewalls, each have a latch flange. Ends of the rims of the second sidewalls, which are directed toward and are adjacent to a same one of the first sidewalls, each have a latch flange. The heat sink includes a channel for slidably receiving one pair of rims of the first or second sidewalls, a blocking member disposed at one end of the channel to block a corresponding sidewall of the fan, and a latch member disposed at the other end of the channel to latch the corresponding latch flanges.

Abstract: A heat dissipating assembly includes a heat dissipating member, a bracket and a locking member. A male connector is coupled to the heat dissipating member with a cable. The bracket includes two securing plates. Each securing plate defines a positioning hole. A locking member is secured to the heat dissipating member and includes a board body. Two locking portions are located on the board body and engaged in the positioning holes. The locking member defines a through opening. Two first locking blocks and two second locking blocks are located on the locking member. The cable is received in the through opening, and the male connector is inserted through the through opening and secured both between the first locking blocks and between the second locking blocks.

Abstract: An axial fan assembly includes a hub, a plurality of connection structures, and a plurality of isolated members. The hub is rotatable about an axis of rotation and includes a radially extending face and a cylindrical portion extending axially from the face. The face includes a radially inner face portion and a radially outer face portion. The plurality of connection structures extends radially inwardly from the radially outer face portion and extends radially outward from the radially inner face portion. The plurality of isolated members extends radially outwardly from the radially inner face portion and is isolated from the plurality of connection structures and from the radially outer face portion by a plurality of slots.

Abstract: A plug assembly is disclosed herein for a borescope inspection path defined through apertures in spaced walls. The plug assembly includes a first plug operable to at least partially close a first aperture in an inner wall. The plug assembly also includes a second plug operable to at least partially close a second aperture in an outer wall. The plug assembly also includes a member extending along an axis and connecting the first and second plugs together in spaced relation to one another along the axis. The member is operable to elastically buckle.

Abstract: A fan includes, an impeller having propeller-shaped blades, a motor disposed inside of a hub to rotationally drive the impeller centered on the rotation axis, a tubular air duct forming an air passage on a periphery of the blades of the impeller and the rotation axis, wherein the rotation axis penetrates the inside of the air duct, and an exhaust outlet larger than an outer diameter of a rotation trajectory of the blades is formed on one end of the air duct, and an air flow guiding plate blocking an opening on an other end of the air duct in the rotation axis direction, a suction inlet through which the rotation axis passes being formed in approximately the center of the air flow guiding plate, wherein the blades are closer to the air flow guiding plate than the air duct.

Abstract: An inducer with an exterior housing and/or interior hub that incorporates grooves or vanes that are helical in nature and in counter rotation with respect to the rotation of the blades of the inducer, which grooves or vanes capture fluid rotating with the inducer blades and use that rotation to guide the fluid up along paths formed by the grooves or vanes and into an impeller, pump or other device.

Abstract: An exhaust-gas turbocharger (1) having a compressor (2) which has a compressor housing (3), a turbine (4) which has a turbine housing (5), a bearing housing (6) between the compressor housing (3) and the turbine housing (5), and a control capsule (7) which has a housing (8) on which is provided a retaining device (9) which interacts with a fastening device (10) on the turbocharger in order to fix the control capsule (6) to the compressor housing (3), the turbine housing (5) or the bearing housing (6). The retaining device (9) is arranged on an outer circumferential region (11) of the control capsule (7), and the fastening device (10) fixes the retaining device (9) in a non-positively locking manner.

Abstract: A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope angle is a slope angle that is operable to prevent flow separation of a fluid passing through the core flowpath.

Abstract: An exemplary geared turbomachine assembly includes a core inlet having a radially inner boundary that is spaced a first radial distance from a rotational axis of a turbomachine, and a compressor section inlet having a radially inner boundary that is spaced a second radial distance from the rotational axis. A ratio of the second radial distance to the first radial distance is of about 0.65 to about 0.9.

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.

Abstract: A turbo-machine inlet includes a gas passage having a non-gradual bend prior to an impeller assembly. The non-gradual bend causes a localized shockwave in fluid flowing through the gas passage.

Abstract: An axial flow fan includes an impeller rotatable about a central axis with a plurality of rotor vanes, a motor that drives the impeller, a base portion that supports the motor, a housing that includes an intake vent, an exhaust vent, and an inner peripheral surface surrounding the impeller and the motor, and a plurality of stator vanes that respectively connects the base portion and the housing, wherein the inner peripheral surface includes a first inner peripheral surface arranged to increase a distance from the central axis toward the intake vent or the exhaust vent in an axial direction, and a recess provided between the first inner peripheral surface and a stator vane included in the plurality of stator vanes and facing the first inner peripheral surface. Thus, airflow is allowed to smoothly pass through the housing, resulting in a decrease in noise generated in the fan.

Abstract: An annular shroud and a wind energy system including the annular wind shroud surround the rotatable constant chord blades of a wind turbine for generating electricity. The wind shroud includes a cylindrical wind tunnel body and a circular structural support ring, wherein the cylindrical wind tunnel body is formed of a plurality of wind tunnel body sector members carried on the circular structural support ring. Each of the plurality of wind tunnel body sector members of the cylindrical wind tunnel body are substantially identically formed. In one form the cylindrical wind tunnel body includes an air horn member on an intake opening edge, a circular cylindrical member, a conical member having a substantially constantly increasing diameter in the wind flowing direction, and a skirt member expanding radially outwardly. In another embodiment, the a conical member smoothly expands in the wind flowing direction.

Abstract: A fan holder adapted for fixing a fan onto a heat sink includes a frame, a fastener pivotedly connected with the frame, and a first resilient member disposed between the frame and the fastener. When the fastener is located at a first position, the first resilient member exerts a resilient force on and keeps the fastener at the first position, and the fan is sandwiched between the fastener and the frame. When an external force is applied on the fastener, the fastener rotates from the first position to a second position in which the fan can no longer be sandwiched between the fastener and the frame, and when the external force is removed, the first resilient member drives the fastener from the second position back to the first position.

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: Turbines, turbine generators, and turbine generator systems are disclosed, which can supply electrical power to an electrical system. A turbine includes a duct including a first opening at a first end, a second opening at a second end, and a depression on an internal surface, as well as a rotor rotatably disposed on the duct and partially disposed within the depression. A turbine generator includes a turbine coupled to a generator. A turbine generator system includes a turbine generator coupled to an electrical system.

Abstract: A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed.

Abstract: A fan assembly includes a bracket and a fan module. The bracket includes a ventilation plate. A limiting portion protrudes from the ventilation plate. The fan module is secured to the ventilation plate and includes a frame and a plurality of fan blades. The frame includes a first sidewall and a second sidewall opposite to the first sidewall. The plurality of fan blades are received in the frame, and each of the plurality of fan blades includes a first edge adjacent to the first sidewall and a second edge adjacent to the second sidewall. A height of the limiting portion is greater than a distance between the first edge and the first sidewall and smaller than a distance between the second edge and the second sidewall.

Abstract: A method for determining the remaining service life of a rotor of a thermally loaded turboengine in which a temperature on the rotor is determined. Thermal stress on the rotor is calculated from the determined temperature, and the remaining service life of the rotor is calculated from the derived thermal stress. The temperature is measured directly at a predetermined point of the rotor, and the thermal stress on the rotor is derived from the measured temperature.

Abstract: An impeller is provided that may be used in compressors or turbines. In another aspect of the present invention, a fiber or a bundle of fibers is woven to form at least two blades of an impeller. Yet another aspect of the present invention employs a peripheral component woven around impeller blades. An additional conductive fiber or bundle of fibers is woven into the impeller in a further aspect of the present invention. Moreover, an aspect of the present invention provides a chilling system that includes at least one compressor, at least one wave rotor, and a refrigerant.