Abstract: A regulatable coolant pump and a method for regulation of this regulatable coolant pump for internal combustion engines, which is driven by way of a pulley actives a valve slide using an electromagnetically activated piston pump equipped with a return spring in the form of a pressure spring. The pump implements a “pump feed” using many small “partial lifts.” A “leakage volume stream” that flows opposite to the “pumped volume stream” is superimposed on the “pumped volume stream” via the arrangement of circular apertures both in the inlet valve membrane of the working piston and in the outlet valve membrane so that the valve slide can be moved in defined manner and in a very robust and reliable manner, with low drive power via the defined superimposition of these two volume streams.

Abstract: A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

Abstract: A ceiling fan includes an annular nozzle having an inner wall, an outer wall extending about the inner wall, an air inlet for receiving an air flow, an air outlet for emitting the air flow, and an interior passage located between the inner wall and the outer wall for conveying the air flow to the air outlet. The inner wall defines a bore through which air from outside the nozzle is drawn by the air flow emitted from the air outlet. The fan includes a support assembly for supporting the nozzle on a ceiling. The nozzle is rotatable relative to the support assembly about a rotational axis and between a first orientation in which the air flow is directed away from the ceiling and a second orientation in which the air flow is directed towards the ceiling.

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: A heat dissipating blower includes a main body and a cover. The main body includes a shell and a fan. An outlet and a first gap are defined in the shell. A connecting portion is set at one end of the first gap away from the outlet. Two sliding grooves are formed on inner surfaces of a first wall and a second wall and a plurality of locating holes is set on the two sliding grooves. The cover includes two parallel side plates and a middle plate. A plurality of positioning pins is set on outer surfaces of the two side plates. Some of the positioning pins are located in corresponding ones of the locating holes to change an area of 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 thermal module includes a centrifugal fan and a circuit board. The circuit board defines a through hole therein. The centrifugal fan includes a top plate located above the circuit board and aligned with the through hole, a first sidewall extending from a circumferential edge of the top plate toward the circuit board, a bottom plate located below the circuit board and aligned with the through hole, a second sidewall extending from a circumferential edge of the bottom plate toward the circuit board, and an impeller. The first sidewall abuts a top surface of the circuit board around the through hole. The second sidewall abuts a bottom surface of the circuit board around the through hole. The impeller is smaller than the through hole. The impeller extends through to be located in the through hole.

Abstract: A power system includes a gas turbine engine, which may include a gear box. The gear box may include a pipe connection configured to receive a removable pipe. The power system may also include a moveable support configured to fasten to the pipe connection to at least partially support the gear box.

Abstract: The flow path of exhaust gas to the turbine wheel (70) of a twin volute turbocharger is influenced by the shape and size of the nozzle formed by the shape (22) of the divider wall (21) and the shape of the flow passage determined by the walls (85, 86) of the turbine housing. By moving the walls (85, 86) toward, or away from the divider wall, the flow of exhaust gas through the nozzle, to the turbine wheel (70) can be modulated, which thus modulates the turbocharger boost pressure. The invention also applies to single volute turbines.

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: A ceiling fan includes an annular nozzle having an inner wall, an outer wall extending about the inner wall, an air inlet for receiving an air flow, an air outlet for emitting the air flow, and an interior passage located between the inner and outer wall for conveying the air flow to the air outlet. The inner wall defines a bore through which air from outside the nozzle is drawn by the air flow emitted from the air outlet. A support assembly supports the nozzle on a ceiling and includes a ceiling mount for mounting the ceiling fan on a ceiling, an arm having a first end connected to the ceiling mount, and a body connected to a second end of the arm and the annular nozzle. The body is pivotable relative to the arm about a pivot axis to move the annular nozzle between a raised and lowered position.

Abstract: The invention relates to a coupling device (14) intended to connect first and second elements (4, 5) which can move relative to one another, comprising a connecting rod (16) coupled to the first and second movable elements (4, 5) at first and second ends (18, 19) respectively, at least one of the ends of the connecting rod (16) having a head (22) intended to cooperate with locking means (23) belonging to the corresponding movable element (5) so as to removably fasten the connecting rod (16) to the corresponding movable element (5), characterized in that the coupling device (14, 15) comprises at least one telescopic guide member (25) serving to support and guide the connecting rod (16) during the movement of the movable elements (4, 5), having first and second ends (28, 26) intended to be attached to first and second support elements (23, 16) respectively.

Abstract: A fan assembly includes a device for creating an air flow and an air outlet for emitting the air flow. The air outlet is mounted on a stand for conveying the air flow to the air outlet. The fan assembly also includes a tilt mechanism for tilting the air outlet relative to at least part of the stand. The tilt mechanism comprises a flexible hose defining, at least in part, an air passage through the tilt mechanism.

Abstract: A method and system for adjusting the clearance between a stator member and the tip of a rotor member in a rotor apparatus. The system comprises a position adjustment mechanism for adjusting the radial position of the stator member to any one of at least two and preferably three different radial positions. The system further comprises a variable pressure chamber having a first pressure state and a second pressure state. The system is arranged for applying a force for maintaining the stator member in either one of said at least two radial positions when said chamber is in said first pressure state and for allowing the position adjustment mechanism to adjust the radial position of the stator member between said at least two positions when the chamber is in said second pressure state.

Abstract: A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor.

Abstract: An insertion/extraction system and method for a compressor casing and a compressor bundle. The system includes a cradle extending from a first axial end of the compressor casing and configured to provide support for the compressor bundle during insertion, and an extension assembly coupled to a first axial end of the compressor bundle and extending therefrom into the compressor casing during insertion of the compressor bundle into the compressor casing, during extraction of the compressor bundle from the compressor casing, or both. The system further includes a support member that engages the extension assembly and the compressor casing to support the first axial end of the compressor bundle via the extension assembly, the support member configured to allow relative movement between the support member and the extension assembly during insertion of the compressor bundle into the compressor casing, extraction of the compressor bundle from the compressor casing, or both.

Abstract: The present invention relates to a jet engine nacelle (1), of the type comprising an aft section forming an external structure (2) which, together with a concentric internal structure (4) comprising an internal panel (10) intended to surround a down-stream portion of the jet engine, defines an annular flow duct for a so-called secondary stream (3), characterized in that exhaust means (11) are formed in the internal panel such that any unwanted excess pressure is discharged into the annular duct.

Abstract: This disclosure relates to a gas turbine engine including a core engine that drives a fan. A fan nacelle surrounds the fan and provides an inner surface facing the fan. The fan nacelle includes an inlet lip adjoining the inner surface. A ring is arranged at the inner surface and is axially upstream from the fan. The ring includes a deployed position in which the ring is spaced radially inwardly from the inner surface to provide a gap therebetween through which air flows. The ring also includes a stowed position in which the ring is arranged radially inwardly from the deployed position and proximate to the inner surface. The ring is commanded to the deployed position in response to detecting a first condition, which corresponds to a flow separation condition at the fan nacelle inlet. The ring may be stowed during cruise conditions, for example.

Abstract: A remote adjustment and measurement system for a steam turbine nozzle assembly is disclosed. In one embodiment, a steam turbine casing segment is disclosed including: a horizontal joint surface; a pocket having a first opening at the horizontal joint surface and a second opening facing substantially radially outward; and a port accessible from a radially outward surface of the steam turbine casing segment, the port fluidly connected to the second opening of the pocket.

Abstract: In an exhaust gas turbocharger for an internal combustion engine of a motor vehicle with a turbine comprising a turbine housing with at least a first and a second spiral channel, each being coupled to an exhaust gas line of an exhaust gas tract of the internal combustion engine for conducting exhaust gas to a turbine wheel arranged within the turbine housing and driving a compressor wheel of a compressor of the exhaust gas turbocharger, an area ratio Qg of the turbine corresponds to the formula Qg=(A?+AAGR)/AR>0.40, wherein A? refers to a narrowest flow cross-section of the first spiral channel, AAGR to a narrowest flow cross-section of the second spiral channel (52b) and AR to a wheel exit flow cross-section of the turbine exhaust channel. The invention further relates to a motor vehicle with an internal combustion engine and such an exhaust gas turbocharger.

Abstract: In one example, a turbocharger for an internal combustion engine is described. The turbocharger comprises a casing containing an impeller having a full blade coupled to a hub that rotates about an axis of rotation. The casing includes a bleed port and an injection port. The full blade includes a hub edge, a casing edge, and a first distribution of angles, each angle measured between the axis of rotation and a mean line at the hub edge at a meridional distance along the hub edge. The full blade includes a second distribution of angles, each angle measured between the axis of rotation and a mean line at the casing edge at a meridional distance along the casing edge. Further, various systems are described for affecting the aerodynamic properties of the compressor and turbine components in a way that may extend the operating range of the turbocharger.

Abstract: A component removal apparatus for use with a turbine engine is provided. The apparatus includes a main body and at least one alignment member that extends from the main body, wherein the alignment member is configured to position the apparatus relative to at least a portion of a component of the turbine engine. At least one leg member extends outwardly from at least one end portion of the main body. At least one lifting member is coupled to the leg member and is configured to apply a force to the leg member and/or the main body to facilitate the removal of the component from the turbine engine.

Abstract: A gas turbine engine has a thrust balance chamber defined between a static housing and a rotating component. The thrust balance chamber is sealed by a first non-contact seal at a radially inner location and a second non-contact seal at a radially outer location.

Abstract: The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterized in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Abstract: A turbine balance assembly has a turbine rotor and shaft. Bearings are positioned radially outwardly of the shaft. A bearing sleeve is positioned radially outwardly of the bearings, and supports the bearings. The bearing sleeve extends along an axial length defined by a rotational axis of the shaft, and has a turbine rotor end adjacent to the turbine rotor, and a remote end. A radially outwardly extending flange on the bearing sleeve extends radially outwardly of a support portion of the bearing sleeve at the turbine rotor end. The flange has a nominal outer diameter, and includes a slot for receiving an anti-rotation tab from a gear cage over a first circumferential extent. A bearing sleeve incorporates the anti-rotation feature, and a gear cage incorporates its portion of the anti-rotation feature. An air turbine starter, and a method of installing components of a turbine balance assembly are also disclosed.

Abstract: A fan assembly for creating an air current includes an air outlet mounted on a stand. The stand includes a base and a body tiltable relative to the base. The fan assembly has a center of gravity located so that when the base is located on a substantially horizontal support surface, the projection of the center of gravity on the support surface is within the footprint of the base when the body is in a fully tilted position.

Abstract: A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.

Abstract: Asymmetric loading within such machines as gas turbine engines can cause distortion of a casing surrounding a rotating assembly. Such distortion may cause rub and therefore inefficient energy usage and shorter operational life. By providing driver arms 112, 212, 312 which extend from radially extending links 113, 213 in a first or high pressure compressor inner casing 101, 201 to a second outer casing 108, compensation for asymmetric loading can be achieved. The casings 101, 201, 108, 208 are presented upon relatively stable bearing supports 102, 110 and therefore, reaction loads are compensated for in order to retain concentricity of the casing 101, 201.

Abstract: An air conditioner includes a case provided with openings, a heat exchanger disposed in the case, one or more fans disposed in the case, and a variation unit that is movably disposed around the fans to vary air inlet and outlet directions.

Abstract: A cooling fan module includes a first cooling fan pivotally connected with a second cooling fan. The second cooling fan is rotatable relative to the first cooling fan between a first state and a second state. The second cooling fan is located on the first cooling fan in the first state. The second cooling fan is located at a lateral side of the first cooling fan in the second state.

Abstract: A tower-internal-equipment bracket structure with a welded structure that can ensure a fatigue strength classification equal to or greater than that of butt welding (BW) or that requires no welding and a wind turbine generator provided with this tower-internal-equipment bracket structure are provided. In a tower-internal-equipment bracket structure provided inside a pole-type steel tower, employing a cylindrical shell (11), to support tower internal equipment, a ring-shaped member (20) having a protruding portion (21) toward the tower interior is interposed, by means of butt welding (BW), between divided portions formed by dividing the cylindrical shell (11) at a desired position in an axial direction, and the protruding portion (21) serves as a bracket-member support portion for the tower internal equipment.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.

Abstract: A compressor casing includes a casing insert with a flexible element in the force flux between the insert wall contour and the outer compressor casing. The flexible element is assembled from a support ring and ribs, wherein the ribs axially in front of the support ring and the ribs axially behind the support ring are arranged in an offset manner in relation to each other. Due to the arrangement of the ribs in an offset manner, the axial force flux between the insert wall contour and the outer compressor casing is deflected twice, and an axially compliant flexible construction is achieved.

Abstract: A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate.

Abstract: The inventive technology, in certain embodiments, may be described as a hydraulic energy converter 1 that comprises: a frame assembly 2 that itself comprises a first frame portion 3 and a second frame portion 4 that is positionally adjustable relative to said first frame portion, said first frame portion affixable in stationary position relative to a water channel structure 5; an axle 6 connected with said second frame portion 4; a driveshaft 7 established substantially orthogonally to said axle 6; waterwheels 8 connected with said axle 6; a gearbox 9 connecting said driveshaft 7 with said axle 6 and established between said waterwheels 8; and at least one rotational energy converting device 10 connected with said driveshaft 7 and said second frame portion 4. A related aspect of the inventive technology—a wind energy converter—may include rotors instead of waterwheels (in addition to perhaps reflecting other differences).

Abstract: A fan assembly includes a motor-driven impeller for creating an air flow, at least one heater for heating a first portion of the air flow, and a casing comprising at least one air outlet for emitting the first portion of the air flow, and first channel for conveying the first portion of the air flow to the at least one air outlet. To cool part of the casing, the casing diverts a second portion of the air flow away from the at least one heater, and comprises a second channel for conveying the second portion of the air flow along an internal surface of the casing. This second portion of the air flow may merge with the first portion within the casing, or it may be emitted through at least one second air outlet of the casing.

Abstract: A gas turbine engine mid turbine frame apparatus includes a an inner case supporting a bearing, an outer case to which the inner case is mounted, and an apparatus for radially positioning one relative to the other, the apparatus including a plurality of radial locators extending outwardly of the outer case and an associated locking apparatus. The locking apparatus is mounted adjacent to but independent of the locators and provides for anti-rotation of the radial locators once installed.

Abstract: A bladeless fan assembly for creating an air current includes a nozzle mounted on a base housing a device for creating an air flow through the nozzle. The nozzle includes an interior passage for receiving the air flow from the base and a mouth through which the air flow is emitted. The nozzle extends about an axis to define an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle includes a surface over which the mouth is arranged to direct the air flow. The surface has a diffuser portion tapering away from the axis, and a guide portion downstream from the diffuser portion and angled thereto.

Abstract: A fan assembly for creating an air current includes an air outlet mounted on a stand. The stand includes a base and a body tiltable relative to the base. The fan assembly has a center of gravity located so that when the base is located on a substantially horizontal support surface, the projection of the center of gravity on the support surface is within the footprint of the base when the body is in a fully tilted position.

Abstract: A fan assembly for creating an air current includes an air outlet mounted on a stand. The stand includes a base and a body tiltable relative to the base. The fan assembly has a center of gravity located so that when the base is located on a substantially horizontal support surface, the projection of the center of gravity on the support surface is within the footprint of the base when the body is in a fully tilted position.

Abstract: Embodiments include a system having a turbine support key having a set of key segments selectively stackable together in a plurality of combinations to adjust a thickness between turbine supports based solely on a selection of the key segments from the set.

Abstract: An axial turbocompressor having an annular compressor passage which is arranged concentrically around a rotational axis, is delimited radially on the outside by a passage wall, and in which rotor blades, which may be assembled to form a ring, are arranged in a rotatably mounted manner around the rotational axis, is provided. The free-ending tips of the rotor blades lie opposite the passage wall in each case, forming a gap, and the passage wall, in the axial section of the tips, at least partially has a wall structuring and wherein a bleed opening of a bleed passage is provided in the passage wall for the tapping of medium flowing in the compressor passage. In order to enable an exceptionally efficient bleed of medium flowing in the compressor passage, the bleed opening is located in the wall structuring.

Abstract: A vibration control apparatus of a wind turbine generator that can be installed in a small space inside a tower, without a weight increase of the tower, and that can change the natural frequency thereof is provided. Included is a swinging rod extending in the vertical direction and suspended from beams provided on an upper part of the tower via a first universal joint; a flange part extending outward from the upper end outer surface of the swinging rod in the radial direction along the circumferential direction; a pendulum including a bob attached to the swinging rod and capable of moving up and down in the vertical direction; and a plurality of attenuation devices each of whose upper end is attached to the beams with a second universal joint and whose lower end is attached to the flange part with a third universal joint.

Abstract: A fan apparatus includes a blower defining an air outlet at a lateral side thereof, an annular guiding rail and a fastener connecting the blower with the guiding rail. The guiding rail defines an annular groove therein. One end of the fastener is received and slidable in the groove of the guiding rail, whereby the fastener can slide in the groove along a circumferential direction of the guiding rail. The other end of the fastener is connected with the blower, and thus the blower is rotatable with respect to the guiding rail such that an orientation of the air outlet of the blower can be easily regulated.

Abstract: An example turbofan engine sound control system includes a core nacelle (12) housing a compressor and a turbine. The core nacelle is disposed within a fan nacelle (34). The fan nacelle includes a turbofan. A bypass flow path downstream from the turbofan is arranged between the two nacelles. A controller (50) is programmed to manipulate the nozzle exit area to control sound propagating from the engine. In one example, the controller manipulates the nozzle exit area using hinged flaps (42) to control engine sound. The hinged flaps open and close to adjust the nozzle exit area and the associated bypass flow rate.

Abstract: A hydropower generating turbine having an impeller housing disposed to receive water, at least one impeller disposed within the impeller housing, at least one adjustable duct pivotally connected to the impeller housing, and, where the duct has a plurality of duct leafs, wherein the duct leafs articulate and cause the duct to converge and diverge for selectively disposing a fluid about the impeller. The ducts may be inflow or outflow ducts, and the turbine may react to a change in the fluid and alter the shape of the impeller. Further, the turbine may have an automated controller where variable change in the flow is detected by a sensor and transmitted to the automated controller to cause a directional shift in the multidirectional turbine.

Abstract: An inner shell for a rotating machine including at least one segment; and at least one complementary segment in operable communication with the at least one segment, the segments forming a support structure for a shroud ring; wherein the at least one segment and the at least one complementary segment are individually moved to change a set of dimensions defined by the at least one segment and the at least one complementary segment. A method for controlling a dimension of the shroud ring in a rotating machine is also disclosed.

Abstract: A mounting apparatus for a blower includes a parallel pair of racks, a pair of sliding rails attached to the racks and capable of sliding along the racks, a pair of seats attached to the rails and capable of sliding along the rails, two pairs of positioning members extending through the racks and engaging with the rails to position the rails on the racks, and a pair of fasteners extending through the blower to engage with the seats to attach the blower to the seats.

Abstract: A combustion air supply blower includes a blower housing having a housing body and housing cover. The cover is removably attached to the housing body and generally provides access to a motor and fan assembly including a fan and a motor. The motor and fan assembly is removably mounted within the housing body and is captured between the housing body and the housing cover such that, upon removal of the housing cover, the motor and fan assembly is exposed and may then be lifted out of the housing body for easy maintenance, repair, and/or replacement of any portion of the motor and fan assembly. Alternatively, upon removal of the housing cover, the motor and fan assembly may be accessed while remaining within the housing body to complete any maintenance and/or repair of the motor and fan assembly.