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 compressor shroud for containing fragments of a compressor impeller and a turbine wheel within a gas turbine engine. The compressor shroud includes a compressor containment section, a turbine containment section, and a containment continuity section. The containment continuity section connects the compressor containment section and the turbine containment section to form a one-piece part.

Abstract: A seal member for use in a channel between a transition seal structure and a vane seal structure in a gas turbine engine. The seal member includes a spring member and a sheathing assembly. A first end of the spring member is affixed to either the transition seal structure or the vane seal structure. The second end is free to move within the channel. The sheathing assembly includes a main body and a plate portion. The main body surrounds the spring member and is affixed to the second end thereof. The plate portion extends from the main body and is adapted to extend toward the other of the transition seal structure and the vane seal structure. The spring member provides a bias on the sheathing assembly such that the plate portion engages the other of the transition seal structure and the vane seal structure to limit leakage through the channel.

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

Abstract: A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a movable actuation rod and a first linkage arrangement which includes a first bell crank connecting the actuation rod to a first component. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank connecting the actuation rod to a second component. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first and the second linkage arrangements are configure so that over a predetermined range of movement of the actuation rod the first component is moved which the second component is not moved.

Abstract: A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud.

Abstract: In accordance with one embodiment, a system includes a multi-stage turbine including a first turbine stage including a first wheel having multiple first slots spaced circumferentially about the first wheel, and multiple first blade segments each coupled to at least one of the multiple first slots. The multi-stage turbine also includes a second turbine stage including a second wheel having multiple second slots spaced circumferentially about the second wheel, and multiple second blade segments each coupled to at least one of the multiple second slots. The multi-stage turbine further includes a one-piece interstage seal extending axially between the first and second turbine stages, wherein the one-piece interstage seal comprises a first radial support coupled to the first wheel and a second radial support coupled to the second wheel, and the one-piece interstage seal extends circumferentially across at least two of the multiple first slots or at least two of the multiple second slots.

Abstract: This invention relates to heat transfer passage (102) within a component (100) and a component having such a heat transfer passage. The passage (102) comprises opposing side walls (112), a base (110) extending between said side walls and one or more upstanding formations (122) depending from said base between said side walls. The passage is arranged to receive a heat transfer fluid flow during use and the upstanding formation (122) is arranged to induce separation of a boundary layer portion of said heat transfer fluid flow from the base in use. The upstanding formation (122) comprises a projection portion (126) which is spaced from said opposing side walls (112). Such upstanding formations are typically referred to as turbulators.

Abstract: An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.

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

Abstract: A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The gas path portion comprises a forward portion forming a leading edge of a stationary vane, an aft portion forming a trailing edge of the stationary vane, and a plurality of middle portions forming a pressure side and a suction side of the stationary vane. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates.

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

Abstract: A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.

Abstract: A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction.

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

Abstract: A turbomachine housing having a parting line is provided. The turbomachine housing has a first housing part with a first parting line bead, which is implemented on the parting line, a second housing part with a second parting line bead which is implemented on the parting line, and a plurality of parting line clamps. The first parting line bead is enclosed together with the second parting line bead by the parting line clamps, so that the first housing part and the second housing part are held together by the parting line clamps using a positive connection on the parting line beads.

Abstract: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend outward from the engine case to the fan case. A front frame assembly includes a plurality of vanes extending radially across the gaspath. A transmission couples a shaft to a fan shaft to drive the fan. A bearing assembly couples the shaft to the front frame assembly. A bearing support extends aftward and radially inward from the front frame assembly to the bearing assembly.

Abstract: A method for monitoring blade frequencies of a wind turbine and a monitoring system for performing the method are provided. An accelerometer or G-sensor is placed into a nacelle of a wind turbine and thereby measuring the vibrations of the nacelle. To extract the vibration signals originating from each blade, the vibration signals are combined with the measuring signals from the azimuth angle sensor (rotating angle), which is normally used for pitch control. To further extract each blade frequency a Fast Fourier Transformation is used on the modulated G-sensor signals. To further monitor a severe and alarming change in each blade frequency, each blade frequency is compared to the other blade frequencies and an alarm is set when a given level is reached.

Abstract: A wind turbine generator is provided in which the efficiency of heating the interior of a nacelle can be improved at a low outside air temperature in a cold region. The wind turbine generator includes a nacelle that accommodates a driving and generating mechanism connected to a rotor head fitted with turbine blades, wherein the nacelle is equipped with a lubricant-oil cooling fan and a generator cooling fan that ventilate the interior of the nacelle to prevent an increase in the temperature of the interior and a heating device that raises the temperature of the interior of the nacelle at a low outside air temperature, wherein the cooling fans can be operated with the rotating directions and the rotational speeds thereof being controlled, and during the operation of the heating device, the rotating directions and the rotational speeds of the cooling fans are controlled so as to make the wind velocity at the ventilation ports thereof about zero.

Abstract: A turbine bucket for a gas turbine engine is described herein. The turbine bucket may include an airfoil, a tip shroud positioned on a tip of the airfoil, and a number of cooling holes extending through the airfoil and the tip shroud. One or more of the cooling holes may include a length of narrowing diameter about the tip shroud and a length of expanding diameter about a surface of the tip shroud.

Abstract: A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice.

Abstract: Contaminant build-up and cooling airflow looses are reduced in a turbine airfoil by joining root and airfoil cooling air passages thereof with a transition passage.

Abstract: A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.

Abstract: A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall.

Abstract: A turbine rotor blade with a platform includes platform cooling channels on the pressure side and the suction side of the platform. The cooling channels are formed from straight section that generally follows a contour of the airfoil in order to provide cooling to as much of the platform surfaces as possible. Pressure side cooling channels have a V-shape from inlet to outlet. Suction side channels branch off from a common channel located along a suction side edge of the platform.

Abstract: The invention relates to a blade for wind-power generators. The inventive blade is divided transversely into two or more independent sections, each section comprising aerodynamic skins or walls (3) and an inner longitudinal reinforcing structure (4). In addition, the ends of the aforementioned sections are equipped with connection means comprising metal inserts (10) which are housed and fixed axially inside the walls of the inner longitudinal resistant structure.

Abstract: An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life.

Abstract: A slurry pump impeller which includes a front shroud and a back shroud each having an inner main face with an outer peripheral edge and a central axis, a plurality of pumping vanes extending between the inner main faces of the shrouds, the pumping vanes being disposed in spaced apart relation. Each pumping vane includes a leading edge in the region of the central axis and a trailing edge in the region of the outer peripheral edges of the shrouds with a passageway between adjacent pumping vanes. Each passageway has associated therewith a discharge guide vane, each discharge guide vane being disposed within a respective passageway and located closer to one or the other of the pumping vanes and projecting from the inner main face of at least one of the or each shrouds.

Abstract: A turbine rotor blade of the spar and shell construction, the spar including a tip end with a dovetail shaped groove extending from the top, and a tip cap includes a dovetail shaped slot that engages with the spar groove to retain the tip cap in place. A shell made from a high temperature resistant material is secured in place between the platform and the tip cap. The platform includes a core extending into a hollow space formed by the shell and discharges impingement cooling air against the backside wall of the shell. The spar and the platform include fir tree configurations so that an assembled blade can be inserted into a slot of a rotor disk.

Abstract: A turbocharger for or in a motor vehicle has a rotor with an intermediate blade disposed between two primary blades. The intermediate blade, at least in some regions, has an angular progression that differs from the primary blades.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing two metallic panels; assembling and joining the two metallic panels to one another to form the aerofoil structure; wherein the two metallic panels each comprise a surface capable of forming an aerofoil and further comprise a root or section thereof which is either integral with or fixed to the aerofoil surface; and incorporating a section of a different material into a part, the said section being made from a material which is different from the material of another part of the aerofoil structure.

Abstract: A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.

Abstract: A propeller fan has a gap between a bellmouth and each blade tip. A leakage flow is thus produced from a positive pressure surface of a blade toward a negative pressure surface of the blade via the gap. The leakage flow develops while flowing from the leading edge of each blade toward the trailing edge, thus forming a blade tip vortex. This increases blowing noise and raises the input of the fan motor. In order to suppress the blade tip vortex caused by the leakage flow, the present invention includes recessed portions and projected portions, which are alternately formed in a portion of a blade surface of each blade corresponding to the blade tip.

Abstract: It is an object of the present invention to provide an ion pump system etc. having a high air-exhausting capacity and vacuum-maintaining capacity and capable of adjusting drive modes suitable for the uses thereof. The subject problem is solved by an ion pump system (7) comprising a casing (1), a first electrode group (2a,2b) provided in the casing (1), a second electrode group (3a,3b) provided on the outer periphery of the first electrode group (2a,2b), and outer magnets (4) for providing a magnetic field in the casing, wherein the first electrode group (2a,2b) and the second electrode group (3a,3b) are constituted as a plurality of layers alternately disposed around the center axis (11) of the casing (1).

Abstract: The present invention is a variable displacement pump system for delivering precisely controlled oil flow and pressure, including a variable displacement pump having an inlet passage, an outlet passage, a first chamber and a second chamber for controlling the displacement of the variable displacement pump. The present invention also includes a fluid control device for receiving fluid from the outlet passage, and selectively delivering fluid to the second chamber. Fluid is delivered from the inlet passage to the outlet passage from the variable displacement pump, and fluid is also delivered from the outlet passage to the first chamber and the fluid control device. When fluid pressure is greater in the first chamber relative to the second chamber, the displacement of the variable displacement pump will decrease, and when fluid pressure is greater in the second chamber relative to the first chamber, the displacement of the variable displacement pump will increase.

Abstract: A compressor system and method of operating same are provided for the compressed air supply of a commercial vehicle, wherein the compressor system includes a compressor for compressed air generation, a transmission for transmitting torque from a drive motor to the compressor, a clutch for disconnecting the connection between compressor and drive motor, and a control unit for opening and closing the clutch. The control unit is capable of opening the clutch in the event a settable maximum allowed compressor speed or motor speed of the drive motor is exceeded and to close the open clutch temporarily when the motor speed is greater than the maximum allowed motor speed.

Abstract: An oil supply system of an automatic transmission includes a first oil pump pumping up oil from the oil reservoir and supplying the oil to the low-pressure part, a low-pressure regulating valve connected to a low-pressure part channel connecting the first oil pump with the low-pressure part, and controlling the pressure of the oil discharged from the first oil pump at pressure required by the low-pressure part, a second oil pump receiving the oil of which the pressure is controlled through the low-pressure regulating valve and supplying the oil to the high-pressure part, and a high-pressure regulating valve connected to a high-pressure part channel connecting the second oil pump with the high-pressure part and controlling the pressure of the oil discharged from the second oil pump at pressure required by the high-pressure part.

Abstract: A downhole pump is operated by a non-electric motor preferably a steam turbine. In a steam assisted gravity drain system the producing well is U-shaped. A steam supply line runs into the turbine that drives the pump after the steam supply passes through a packer. The steam exhaust runs through a shroud until the U-shaped well turns back to go up to the surface. Pump suction is thus separated from steam discharge to reduce mixing as the path of least resistance for the discharged steam when it exits the shroud is up to the surface. The exhaust steam keeps the produced fluids warm and flowing. An injector well runs parallel and slightly above the horizontal portion of the U-shaped producing well.

Abstract: A suction pump, in particular a breast pump, comprises a bleed valve with a bleed opening, a bleed body which seals the bleed opening and an electromagnet for operating the bleed body. The bleed body may be operated such that upon opening the valve initially only a partial region of the bleed opening is released and subsequently a greater part thereof or the whole bleed opening is released. The suction pump provides a large functionality with the smallest size and, furthermore, is cheap to produce and easily assembled.

Abstract: A fluid pump for a fuel dispensing unit comprises a pump housing with a first chamber and a second chamber, each chamber having a fluid inlet valve and a fluid outlet valve, respectively. The chambers are separated by a movable piston arranged to repeatedly decrease and increase the volumes of the chambers. The piston comprises a magnetic device, and an electromagnetic control configured to move the piston by altering a magnetic field, for repeatedly decreasing and increasing the volume of the chambers. A controllable fluid flow passage connected to first chamber and to the second chamber that allows fluid to pass from the first chamber to the second chamber without passing through the any of the fluid inlet valves or the fluid outlet valves so that when there is a flow of fuel from the first chamber to the second chamber via the fluid flow passage and when the piston moves towards the first side the first outlet valve and the second inlet valve remain closed during operation.

Abstract: A pump and a method for operating a pump is proposed for mounting an impeller, which is inexpensive, free from contact and wear and thus extremely permanent. For this the invention uses a combination of permanent magnetic bearings and flow-mechanical bearings. The mounting is thus based on purely passive elements without using actively controlled and/or regulated elements.

Abstract: A rotary blood pump includes a casing defining a pumping chamber. The pumping chamber has a blood inlet and a tangential blood outlet. One or more motor stators are provided outside of the pumping chamber. A rotatable impeller is within the pumping chamber and is adapted to cause blood entering the pumping chamber to move to the blood outlet. The impeller has one or more magnetic regions. The impeller is radially constrained in rotation by magnetic coupling to one or more motor stators and is axially constrained in rotation by one or more hydrodynamic thrust bearing surfaces on the impeller.

Abstract: A cassette for use with an ophthalmic surgical pump for collecting aspirant fluid and tissue from a patient's eye includes a rigid walled container having an interior volume. At least one tapered alignment slot is formed in a side wall of the container and extends from a back wall towards a front wall. An irrigation and aspiration manifold base is removeably attached to the container. An aspiration path is formed within the container for receiving the aspiration fluid and the tissue from the eye and directing the flow of fluid towards a front half of the container before the fluid and tissue collects within a majority of the interior volume of the container. A fluid level indicator is formed on a wall of the container, such that an associated photo-detector of the pump may determine a level of fluid in the container.

Abstract: This refrigeration compressor includes a plurality of compression units, each compression unit having a cylinder head including a refrigerant suction chamber and a refrigerant discharge chamber, a refrigerant distribution device having a distribution pipe and bypass pipes putting the distribution and the suction chambers of the compression units in communication, and a refrigerant discharge device having a discharge pipe and bypass pipes putting the discharge pipe and the discharge chambers of the compression units in communication. The compressor also includes a pressure equilibration pipe arranged to put the suction chambers of at least two compression units and/or the discharge chambers of at least two compression units in communication.

Abstract: The present invention provides a dry pump including: a center cylinder which includes: a plurality of pump chambers containing an upper stage pump chamber that communicates with an intake port and a lower stage pump chamber that communicates with a discharge port; a plurality of rotors contained in the plurality of the pump chambers; a rotating shaft that is a rotation axis of the rotor; and a side face on which a communication hole is formed, the side face being intersected by the rotating shaft extending in the axial direction, and being provided adjacent to the lower stage pump chamber, and a side cover which covers the side face with the communication hole to form a space.

Abstract: A compression mechanism is configured to be used in a scroll compressor. The compression mechanism includes a fixed scroll and a movable scroll. One of the fixed scroll and the movable scroll is a cast iron molding fabricated through semi-molten die casting, and the other of the fixed scroll and the movable scroll is a grey iron casting.

Abstract: A hydraulic device has an inlet side and an outlet side and includes two meshing cogwheels. Each cogwheel has external oblique teeth and is arranged between an inlet side and an outlet side. At least one control groove is provided on an end side of the cogwheels. The control groove periodically produces a pressure equalizing connection during the rotation of the cogwheels.

Abstract: In a screw compression apparatus in which shaft sealing members (13, 14) isolate a bearing space (7, 8) from a rotor chamber (5) and a lubricating fluid separating collector (3) separates the rotor lubricating fluid from the target gas discharged by the screw compressor (2), rotor lubricating fluid separated by the lubricating fluid separating collector (3) is introduced into the rotor chamber (5) via a rotor lubricating flow channel (25), and a bearing lubricating system (17) supplies a bearing lubricating fluid to the bearing space (7, 8). The bearing lubricating fluid flowing out from the bearing space (7, 8) is cooled and returned to the bearing space (7,8). A part of the target gas may be supplied to the shaft sealing members (13, 14) at a location between carbon rings of the shaft sealing members.