Abstract: Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.

Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Abstract: A fluid diverter that utilizes a gland seal. The gland seal includes a stationary seat, a first O-ring, a rotating seal face, a second O-ring, a plurality of tabs, and a spring retainer. The fluid diverter may also include a one-piece bearing isolator. The one-piece bearing isolator includes a stator having a first end, a first set of O-rings, a second set of O-rings, and a second end. The one-piece bearing isolator also includes a rotor seated in the stator, the rotor including a recess, an O-ring positioned in the recess, and a lip extending over and hugging the stator. The fluid leak diverter utilizes the gland seal and one-piece bearing isolator to direct leaked liquid fluid away from a pump (and functional components of the pump such as bearings).

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: A bleed valve has a valve body enclosing a valve chamber defining a passageway between an inlet port and an outlet port. A panel is mounted into the valve body. The panel is deflectable under fluid pressure between a sealing position blocking the passageway when the bleed valve is in a close state, and a bleeding position allowing fluid flow communication between the inlet port and the outlet port when the bleed valve is an open state. A pressure control device is provided to vary a fluid pressure differential between opposite sides of the panel within the valve chamber and selectively open or close the bleed valve.

Abstract: The engine is adapted to generate thrust or designed to generate torque includes a combustor, the combustor generates an exhaust gas flow to push the rotor blades of a rotor in a rotor housing, the exhaust gas flow rotates the rotor, shaft, and fan which produces a rotating force and produces an air flow. The rotor housing having a first wall, a second wall, and a third wall which guides the exhaust gas flow until the exhaust gas flow reaches a housing gap at the second wall and the exhaust gas flow moves out from the rotor housing, while the first wall having another housing gap for the air flow to go through to cool the rotor and the cooling process adds torque to the engine. The engine includes an optional wind turbine assembly. An air compressor is either driven by an electric motor or driven by other means.

Abstract: An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. A primary air flow path is defined between a primary inlet and a primary outlet. Air in the primary air flow path can flow into a secondary air flow path or rotate the turbine, that converts energy from the air flow to rotational mechanical energy. Air in the secondary air flow path can pass through at least a first cavity and first passage before rejoining the primary air flow or joining ambient air.

Abstract: A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

Abstract: Discloses is a hermetic blower for high-temperature gas, including: a blower unit in which the inside is hermetic so as to prevent an internal working fluid from being leaked to the outside; a motor unit supplying power to the blower unit; and a magnetic coupling unit connecting the blower unit and the motor unit by using a magnetic force.

Abstract: A guide vane for a variable turbine geometry and a turbine assembly provided with same are described. The guide vane has an outer face that is at least partly concave in design. The inner face opposite the outer face may also be at least partly concave in design. This gives the guide vane a good functional capability when arranged in a vane ring of a turbine, since an overflow through the gap between the guide vane and the neighboring walls is reduced.

Abstract: A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90° from the base portion. The first and second walls extend towards one another.

Abstract: A dishwashing appliance having a vibration-reducing mounting assembly is provided herein. The dishwashing appliance may include a tub defining a wash chamber, a sump, and a fluid pump. The sump may be positioned at a bottom portion of the tub along a vertical direction. The sump may include a bottom wall defining a recessed chamber. The fluid pump may be in fluid communication with the recessed chamber of the bottom wall. The fluid pump may include a fluid impeller, an electric motor, and a volute cover. The fluid impeller may be rotatably positioned within the recessed chamber. The electric motor may be in mechanical communication with the fluid impeller to motivate rotation thereof. The electric motor may be positioned above the fluid impeller. The volute cover may be positioned between the electric motor and the fluid impeller along an axial direction.

Abstract: There is disclosed a controlled gap seal for a gas turbine engine. The seal has a ring annularly and continuously extending about a central axis. A runner that is configured for rotation about the central axis and rotatable relative to the ring. The runner has a face facing a face of the ring. The face of the ring is spaced apart from the face of the runner by a gap. Surface discontinuities are circumferentially distributed around the central axis. The surface discontinuities are located at specific locations and distributed in specific ways. A method of using the controlled gap seal is disclosed.

Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.

Abstract: A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side. A first wall is circumferentially spaced from a second wall. The first and second wall extend outward from the base portion and are connected by an outer wall to define a passage that extends in a generally axial direction along the base portion.

Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

Abstract: The invention relates to a seal arrangement for sealing a radial gap between an inner first component (8) and an outer second component (15) which can be rotated in relation to each other, the first component (8) being rotatable about an axis of rotation and the second component (15) being arranged coaxially to the first component (8). The seal arrangement comprises: a dynamic seal part (14) connected to the first component (8); a static seal part (15) connected to the second component (15); a first labyrinth seal (1) formed by a gap between a first section of opposing surfaces of the dynamic seal part (14) and the static seal part (15); and a leaf seal (2) which is radially arranged inside the first labyrinth seal (1). The invention is characterised in that the seal arrangement comprises a dust protection cover (3) connected to the second component (15), which is arranged radially outside the first labyrinth seal (1).

Abstract: An exhaust-gas turbocharger for an internal combustion engine has a turbine housing, in which a turbine wheel with a shaft is arranged rotatably. The shaft is mounted rotatably in a bearing housing via at least one piston ring adjacently with respect to the turbine wheel. The bearing housing has a lubricant inflow and a pressureless lubricant outflow for lubricating the shaft, wherein an insulating washer is provided which is clamped in by the turbine housing and the bearing housing and has an opening which is connected to the lubricant outflow in a manner which conducts a lubricant. Passage of lubricant out of the bearing housing into the turbine housing is avoided.

Abstract: A pump includes first and second impellers and a sealing element. The sealing element is arranged between the first and second impellers around the drive shaft. The sealing element has a first end transvers to the drive shaft and facing the first impeller and a second end transverse to the drive shaft facing the second impeller. The sealing element has a length along an axis smaller than the distance between the first and second impellers such that the sealing element is movable along the axis between the first and second impellers. The first and second ends of the sealing element have first and second areas transverse to the axis, the first area being larger than the second area such that the force exerted by the lower pressure generated by the first impeller is substantially equal to the force exerted by the higher pressure generated by the second impeller.

Abstract: A support structure for a gas turbine engine includes an axially extending portion that forms a loop. A radially extending portion extends radially inward from the axially extending portion. A plurality of retention members are attached to at least one of the axially extending portion and the radially extending portion for retaining a blade outer air seal.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.

Abstract: A turbo machine, such as a gas turbine, includes a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure. The turbo machine includes a metal casing, whereby an electrical heating system is provided on the lower half of the metal casing. A safe operation is achieved by having the heating system configured as a redundant system.

Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.

Abstract: A turbo compressor includes: a compressor casing which accommodates impellers compressing gas by rotation; and a motor casing which accommodates a motor rotating the impellers, wherein the motor casing has a cylindrical main body part having a larger diameter than a mounting flange provided in the compressor casing, and the compressor casing and the motor casing are connected through an adapter member.

Abstract: In a heat shield for an exhaust gas turbocharger, by means of which at least a first area of the exhaust gas turbocharger is to be shielded against a second area in a heat insulating manner wherein the heat shield comprises at least one fastening structure by which the heat shield is attached to one of the housing parts of the exhaust gas turbocharger, the fastening structure is in the form of locking elements for interlocking the heat shield with the respective housing part. The invention also resides in an arrangement of a heat shield between two housing parts of an exhaust gas turbocharger in such a way that it is firmly attached to one housing part without contacting the other housing part.

Abstract: An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.

Abstract: A method of controlling the part-load performance of a turbine includes generating a bypass flow in the turbine by removing a portion of a compressed fluid from a compressor of the turbine, determining an operating load of the turbine, transmitting the bypass flow to a turbine section of the turbine; and selectively heating the bypass flow according to the determined operating load of the turbine.

Abstract: Disclosed is a dental handpiece structure including a head having a turbine chamber, a rotor installed in the turbine chamber and having a transmission shaft, and a transmission element composed of a plurality of turbine vanes. A high-pressure air entering into the turbine chamber can push each turbine vane to drive and rotate the rotor, and a breach is upwardly formed between two adjacent turbine vanes. A head cap is covered onto the turbine chamber, and a circular groove is formed at the head cap and between an end surface facing the turbine chamber and the transmission element, and the circular groove and each breach are arranged opposite to each other for collecting the high-pressure air guided out from each breach to enhance the cutting force of the dental handpiece.

Abstract: An aspirating face seal for use with a rotary machine includes a rotating seal ring including a radially outer surface that includes an oblique portion. A stationary seal ring is coupled proximate the rotating seal ring such that a first gap is defined therebetween. The stationary seal ring is movable along a centerline axis of the rotary machine between an open position and a sealed position, and includes an extension member that extends across the first gap. An auxiliary seal includes at least one seal tooth that includes a seal tooth tip. The at least one seal tooth extends radially inward from the extension member such that a second gap is defined between the seal tooth tip and the oblique portion.

Abstract: A sealing arrangement, for example for providing an intershaft seal between shafts of a gas turbine engine, includes an air-riding sealing ring disposed between runners. A buffer fluid, such as air, is conveyed to a buffer cavity through a passage in the sealing ring. The buffer air provides a positive pressure drop along fluid-riding gaps, preventing leakage across the sealing arrangement. The sealing ring may be a split carbon ring, and measures may be provided to minimize leakage of buffer air at the split.

Abstract: A plurality of blades are studded in a rotor disc integrated with the rotor along the circumferential direction of the rotor, a plurality of vanes are attached to a casing covering the rotor along the circumferential direction of the rotor, and an internal diaphragm disposed on rotor-side surfaces of the vanes in such a way that the internal diaphragm faces the rotor disc. The vanes and the blades adjacent to each other in the axial direction of the rotor form a turbine stage. A rotor-side cooling path is formed through the rotor disc in the axial direction of the rotor, and a diaphragm-side cooling path is formed through the internal diaphragm in the axial direction of the rotor, and a cooling medium flowing through the rotor-side cooling path diverts into the diaphragm-side cooling path and a labyrinth flow path provided between the internal diaphragm and the rotor.

Abstract: A system and method for sealing a shaft disposed for rotation within a casing, where two axially-spaced seal rings of an oil film seal extend around the shaft and define a clearance therebetween. Oil is pumped into the clearance from an oil reservoir and a portion of the oil is received in an annular port defined in the casing between an outer labyrinth seal and one of the axially-spaced seal rings. The oil mixes with a process gas to for an oil and gas mixture. A blower is in fluid communication with the annular port and circulates the oil and gas mixture to a trap where the oil is separated from the process gas and a separated process gas is returned back to the annular port.

Abstract: An example blade outer air seal assembly includes a blade outer air seal that is biased toward a second part. The blade outer air seal and the second part move together radially during operation. Radial inward movement of the blade outer air seal is limited exclusively by the second part during operation.

Abstract: An exemplary turbomachine seal assembly includes a ring seal that has a radially-facing sealing surface, an axially-facing sealing surface, and a first tapered surface. The turbomachine seal assembly also includes a spacer that has a second tapered surface. The second tapered surface interfaces with the first tapered surface to bias the radially facing sealing surface and the axially facing sealing surface toward a sealing position.

Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.

Abstract: A seal assembly for a fan duct metering valve disposed within a casing of a gas turbine engine includes a tab for extending through an opening in the casing and attaching to the valve, a carrier for extending into the opening and engaging the valve such that fluid does not leak between the valve and the carrier.

Abstract: A centrifugal compressor for compressing a refrigerant vapour in a refrigeration cycle. The compressor comprises an impeller drive shaft (28) supported by first and second radial bearings (32) for rotation within the compressor housing and an impeller assembly including at least one centrifugal impeller wheel mounted on the impeller drive shaft to rotate with the impeller drive shaft. The first and second radial bearings are hydrodynamic fluid bearings in which the bearing fluid is the refrigerant vapour. The compressor further comprising a conduit (36) for supplying a portion of the refrigerant vapour from the impeller assembly to the first and second fluid bearings.

Abstract: Disclosed herein is a fan module including an impeller cover having an intake member formed therein and covering one side of a housing, an impeller accommodated within the impeller cover and rotatably coupled to a rotational shaft of a motor accommodated in the housing, and a leakage reduction member positioned in an inner surface of the impeller cover to reduce a flow leakage between the impeller cover and the impeller.

Abstract: This hydraulic machine (1) has a wheel (2) mounted to move in rotation relative to a stationary structure (9) and about a stationary axis of rotation (X2), the wheel (2) being designed to pass a forced flow (E) of water therethrough. A hydrostatic bearing (100), provided between firstly an element (111) constrained to rotate with the wheel (2) and, secondly a portion (91) of the stationary structure (9), is disposed between a first zone (Z1) of the machine, which zone is in fluid communication with the forced flow (E) and in which zone, during operation, a pressure prevails that is similar to the pressure of the forced flow, and a second zone (Z2) of the machine that is isolated from the forced flow by said bearing.

Abstract: A sealing structure in which free-cutting spacers on a sealing base plate and sealing fins on a rotor are opposed to each other is provided. The sealing base plate is disposed so as to be movable in an axial direction of the rotor. When a steam turbine increases in load, a pressure head moves in an axial steam-pressure loading direction of the rotor and the sealing base plate connected to the pressure head moves in the axial steam-pressure loading direction. Since the free-cutting spacers at positions opposed to those of the sealing fins existing after the movement of the sealing base plate are maintained in a non-contact state, clearances between the sealing fins and the free-cutting spacers are dimensionally minimized.

Abstract: A propeller pod drive for a vessel has at least one driveshaft for driving a propeller, at least one radial bearing arrangement for receiving radial forces, at least one axial bearing arrangement for receiving axial forces of the driveshaft. A thrust collar is supported in axial direction on at least one side in axial direction at a guide device, and a supporting structure for arranging the at least one radial bearing arrangement and the axial bearing arrangement. The guide device has at least three, axial sliding segments arranged in a segment guide and each of which has a sliding surface in contact with the thrust collar.

Abstract: A bearing foil assembly includes a top foil, an intermediate foil, and a bump foil. The bump foil is provided with corrugations at circumferentially spaced locations. The bump foil has an end that is bent radially outwardly from a center of the foil assembly. The top foil has a bent portion extending radially outwardly and adjacent to the bent end of the bump foil. A first radius of curvature is defined to a curved portion leading into the bent portion at a first end adjacent to the bent end. A second radius of curvature is defined at an end of the bent portion on an end opposed to the bent end. A ratio of the first radius of curvature to the second radius of curvature is between 0.6 and 10. A bearing assembly, a shaft sub-assembly, an air machine, and a method of assembling a bearing into an air machine are also disclosed.

Abstract: A lower plate includes a lower air inlet arranged radially outward of a bearing portion. In a plan view, a plane is divided into four regions by a first straight line which is parallel to an air outlet and crosses a central axis and a second straight line which is perpendicular to the air outlet and crosses the central axis, and one of the four regions in which a tongue portion is arranged is a first region, followed by a second region, a third region, and a fourth region in this order in a rotation direction of the blades. The air outlet is arranged to extend over both the first and fourth regions.

Abstract: A dry seal apparatus (30) for a machine (10) includes a seal having a stationary portion (40) and a rotating portion (38); a space (44) disposed between the stationary and rotating portions; a biasing member (42) disposed proximate the stationary portion (40) and in contact therewith for applying a force to the stationary portion; and a labyrinth (37) proximate the rotating portion (38) and constructed and arranged for receiving a liquid for being vaporized before entering the space between the stationary and rotating portions of the seal. A related method is also provided.

Abstract: Arrangements for promoting the restriction of fluid flow along a shaft via providing a deformable ring member in an annulus between the shaft and housing. In an initial general condition, the deformable ring member permits free fluid flow in a general direction along the shaft while in a second, constricted condition, the deformable ring closes or blocks a gap or clearance normally conducive to free fluid flow to thereby restrict fluid flow. An actuation medium, which can take any of a very wide variety of forms, preferably promotes constriction of the deformable ring member directly or indirectly.

Abstract: A method of deploying offshore wind turbine assemblies includes mounting a wind turbine assembly horizontally on a vessel and transporting the wind turbine assembly to an offshore site. The wind turbine assembly is raised to a vertical condition at the site and attached to anchor weights. Blades are attached to the turbine head after the wind turbine assembly is in the vertical condition. In one embodiment, the wind turbine assembly can include a tower including tapered lower and upper sections joined together at their respective wide ends, a turbine head connected to the upper section, and a platform connected to the lower section. The platform includes a buoy tank partially filled with ballast to provide mass and buoyancy. A wave piercing cowling is rotatively attached to the lower section. The turbine head can include an adjustable journal bearing, scabbard blade mounts, and a gearless induction generator with flux adjusting capabilities.