Abstract: Systems, methods, and software for determining impedance of a casing-cement bond are described. In some aspects, the bond impedance is determined based on results of comparing a measured waveform and a model waveform. The model waveform corresponds to an estimated impedance of the bond and corresponds to a ray tracing of an acoustic signal that accounts for a radiation pattern of the acoustic transmitter and a curvature of the well casing. The measured waveform and the model waveform are generated based on operating an acoustic transmitter and an acoustic receiver within a wellbore comprising the well casing.

Abstract: Methods and apparatus for transmitting power and data along a metal pipe using wideband acoustic waves. Arrangements use shear-horizontal waves, transmitting narrowband signals for power applications and wideband signals for communications having a bandwidth greater than the coherence bandwidth of the acoustic-electric channel. Chirp wave signals, direct sequence spread signals, and on-off keying are used. Acoustic-electric channels include wedges fixed to a pipe or other substrate, transducers fixed to the wedges, and electronics linked to each transducer for sending and receiving power and signals. Matching networks, rectification circuits, and non-coherent signal reception methods may be used.

Abstract: Downhole assemblies including a plurality of tubular members extendable within a wellbore and defining a through bore. A telemetry device is positioned within a wall of one of the plurality of tubular members and has a secondary flow path defined therethrough and a valve element engageable with a valve seat provided at an upper end of the secondary flow path. The secondary flow path extends between an inlet and an outlet, both of which fluidly communicate with the through bore and are defined in the one of the plurality of tubular members. A flow restrictor is located within the through bore and is axially positioned between the inlet and the outlet of the secondary flow path. The valve element is actuatable to control fluid flow through the secondary flow path to selectively generate a fluid pressure pulse.

Abstract: Systems and methods are disclosed for obtaining distance-related wellbore parameters using pulse-echo measurements. For example, the depth of a wellbore may be computed and/or the length of a tubular string positioned in a wellbore may be determined.

Abstract: An optical analysis tool includes an integrated computational element (ICE). The ICE includes a plurality of layers stacked along a first axis. Constitutive materials of the layers are electrically conductive and patterned with corresponding patterns. An arrangement of the patterns with respect to each other is related to a characteristic of a sample.

Abstract: An in-well type sampling system including a sampling chamber actuable to receive a fluid sample and a pressure source coupled to the sampling chamber to supply pressure to the sampling chamber after the sampling chamber actuating. A pressure sensor is provided in communication with the pressure source to measure the pressure of the pressure source. A telemetry communicator is coupled to the pressure sensor to send a signal from the pressure sensor away from the sampling system.

Abstract: A mining machine includes a cutting mechanism with an arm, and a substantial weight of more than a thousand pounds attached to the arm. The mining machine also includes a first disc cutter adapted to engage the material to be mined and mounted on a first disc cutter assembly for eccentrically driving the first disc cutter, the first disc cutter assembly being mounted within the substantial weight. The mining machine also includes at least a second disc cutter spaced apart from the first disc cutter assembly and adapted to engage the material to be mined, and mounted on a second disc cutter assembly for eccentrically driving the second disc cutter, the second disc cutter assembly being mounted within the substantial weight.

Abstract: The method for reciprocating punching/raking/loading by a power box on an excavator and the excavator having a power box capable of reciprocating punching/raking/loading, which includes a reciprocating impact power box body and a reciprocating impact box raking device, the reciprocating impact box raking device includes a raking rotary member disposed on the lower portion of the side face of the reciprocating impact power box body and a raking rotary arm disposed on the raking rotary member and driven by it to rotate, the raking end of the raking rotary arm disposed on the reciprocating impact power box body rotates relative to the reciprocating impact power box body to rake the material to an area beyond the surface of the reciprocating impact power box body, the raking rotary arm rakes up the material punched by a reciprocating impact head and moves the material to a material-clearing portion.

Abstract: The present invention relates to a self-propelled construction machine, in particular a road milling machine, a recycler or a surface miner, comprising a machine frame 1 supported by a chassis 2 which comprises front and rear running gear 3, 4. A working device 5 is arranged on the machine frame 1 and comprises a working roller 17 for working the ground. Lifting devices 15, 16 are associated with the individual running gears 3, 4 and can each be retracted or extended for raising or lowering the running gears with respect to the machine frame. In addition, the construction machine comprises a control unit 20 for actuating the lifting devices 15, 16, which control unit comprises a lifting position measuring device 22 for detecting the lifting position of the lifting devices and a tilt detection device 23 for detecting the tilt of the machine frame 1 transversely to the working direction A of the construction machine.

Abstract: The method for directionally swaying and resetting harrow teeth of a rolling harrow loader-excavator and the rolling harrow loader-excavator comprising a harrow rotary piece, directional sway and reset harrow teeth, a harrow supporter, a driving mechanism, a feeder mechanism and a body; each directional sway and reset harrow tooth comprises a torsion spring shaft supporting piece, a tooth handle sway limiting piece, a directional sway and reset tooth handle, a directional sway and reset tooth point, a torsion spring tooth handle shaft, a torsion spring and a torsion spring tooth handle shaft retaining piece.

Abstract: A pump device includes a shaft, a first gear pair, a second gear pair, a support pin, and a casing. The first gear pair includes a first driving gear which is disposed on the shaft and is rotatable together with the shaft, and a first driven gear driven by the first driving gear. The second gear pair includes a second driving gear which is disposed on the shaft coaxially with the first driving gear and is rotatable together with the shaft, and a second driven gear driven by the second driving gear and arranged coaxially with the first driven gear. The support pin penetrates the first driven gear and the second driven gear and rotatably supporting the first driven gear and the second driven gear. The casing covers the first gear pair and the second gear pair. The support pin is fitted to the casing to be fixed.

Abstract: A wheel of a turbocharger includes a first end opposite a second end and a rotational axis extending between the first end and the second end. The wheel also includes a back wall located at the second end and a balance groove formed in the back wall. The balance groove has a plurality of side walls and a bottom surface. The side walls and the bottom surface of the balance groove are milled surfaces.

Abstract: A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.

Abstract: A template is provided that may include a body having an interior surface shaped to substantially mate with an exterior surface of at least a portion of an airfoil. At least one machining tool positioning member is positioned on the body and configured to locate a machining tool for operation on the airfoil. In another embodiment, the template may include a longitudinal slit allowing selective placement and selective removal of the body from the airfoil, and/or a longitudinal positioning element at an end of the body for positioning the template relative to an endwall of the airfoil.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

Abstract: A turbine blade for a gas turbine has a securing region and a platform region that adjoins the securing region and has a platform on which a blade airfoil with a profiled cross-section and with a pressure-side wall and a suction-side wall is arranged, wherein each outer face of the pressure-side wall and/or the suction-side wall transitions into the platform surface via an outer rounded section. The turbine blade also has at least one cavity which is arranged in the blade airfoil and extends into the platform region and in which at least one rib is provided that connects the pressure-side wall to the suction-side wall, the rib extending along a longitudinal direction of the blade airfoil so as to divide the cavity. At least one slot is introduced into the rib in the platform region, the rib passing through the rib and being arranged in the longitudinal direction.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine comprises using a capping panel to cover a pocket in a pocketed aerofoil body. The pocketed aerofoil body has a ledge of substantially constant thickness that extends around its perimeter, and to which the capping panel is joined (e.g. welded) during manufacture. This ensures that the geometry of the join is consistent around the perimeter, meaning that the resulting join has improved properties, for example in terms of residual stress and/or distortion.

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

Abstract: Article includes a substrate, a bond coat disposed on the substrate, an environmental barrier coating disposed on the bond coat, and a patterned abradable coating disposed on the second top coat. The environmental barrier coating includes an intermediate layer disposed on the bond coat, a sealing layer disposed on the intermediate layer, a first top coat disposed on the sealing layer, and a second top coat disposed on the first top coat. The first top coat is different from the second top coat.

Abstract: A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot. The keyway restrains the first wedging body against movement in the axial direction. The first wedging body further has a first angled surface over which a correspondingly angled leading end surface of the root slides when the root is inserted in the slot to urge the leading end of the root radially outwardly.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root.

Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.

Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

Abstract: A compressor assembly is disclosed. The compressor assembly may have a compressor housing. The compressor assembly may also have a compressor impeller disposed within the compressor housing. Further, the compressor assembly may have a bearing housing attached to the compressor housing. The compressor assembly may also have a diffuser ring disposed between the compressor housing and the bearing housing. In addition, the compressor assembly may have at least one tab. The tab may extend radially outward from the diffuser ring. The tab may be configured to engage with a recess in the compressor housing. The compressor assembly may also have at least one fastener. The fastener may be configured to attach the diffuser ring and the compressor housing.

Abstract: A mounting device for mounting a guide blade to be mounted in a blade groove of a turbine, where the mounting unit has a clamping unit and a pressing unit. Here, the clamping unit is designed to produce in the blade groove a non-positive connection in a circumferential direction. The pressing unit is arranged behind the clamping unit in the circumferential direction and the pressing unit is supported against the clamping unit in the circumferential direction. The pressing unit is designed to apply a pressing force by means of a pressing piston in an opposite direction to the circumferential direction in a mounting direction and to transmit said force to the guide blade to be mounted.

Abstract: A face seal includes a seal carrier defining an axis and having a pilot flange, a seal element disposed at least partially in the seal carrier, and a retaining plate connected to one axial end of the seal carrier. The retaining plate has an axial step disposed circumferentially about the retaining plate. The axial step is interfaced with the pilot flange.

Abstract: An assembling method of a seal structure of a rotary machine includes inserting a pin member into a through hole formed in a cylindrical member; threadably fitting the pin member into a pin installation hole of a segment; inserting a locking member into a first pin hole formed in the segment and a second pin hole formed in the pin member and fixing the pin member to the segment; arranging the segment in a groove part; inserting the cylindrical member; positioning the cylindrical member by causing the cylindrical member to slide in the axial direction; fixing the cylindrical member with respect to a seal mounting hole; causing the pin member to engage with a temporary joint member; moving an outer circumference side member and an inner circumference side member to approach to each other in the radial direction; and taking out the temporary joint member.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: A sealing system includes a bolt and a cover plate for sealing a joint between a rotor disk and a blade root of a rotor blade, the blade root being disposed in a blade root slot in the rotor disk. The sealing arrangement is used in particular in a gas turbine.

Abstract: A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.

Abstract: An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.

Abstract: A turbocharger is provided that includes a turbine housing including a gas inlet passage. A turbine wheel has a plurality of blades and is arranged in the turbine housing. A bearing housing is connected to the turbine housing. A shaft is rotatably supported in the bearing housing and connected to the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel, the shroud being arranged in spaced relation from and not in contact with the turbine housing. A fastening system secures the shroud relative to the bearing housing. The fastening system is configured to fracture when a force is exerted on the shroud corresponding to at least a portion of the turbine wheel contacting the shroud.

Abstract: An inner fixed structure for an aircraft nacelle may comprise a nanoreinforced polyimide composite skin. The nanomaterials may increase thermal conductivity and decrease microcracking in the inner fixed structure. The inner fixed structure may comprise an inner polyimide composite skin, an acoustic core, and an outer polyimide composite skin. The inner fixed structure may be blanketless.

Abstract: A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies.

Abstract: A turbocharger is provided that includes a turbine, a compressor and a bearing housing disposed and connected between the turbine and the compressor. A shaft is rotatably disposed within the bearing housing and extending into the turbine and the compressor. A bearing arrangement is disposed between the shaft and the bearing housing and includes a inner bearing race element and an outer bearing race element. The compressor wheel includes a hub having a collar portion with a bore therein for receiving an end of the shaft. An end portion of the inner bearing race element is arranged to engage an outer circumferential surface of the collar portion.

Abstract: A turbocharger is provided that includes a turbine, a compressor and a bearing housing disposed and connected between the turbine and the compressor. A shaft rotatably disposed within the bearing housing and extending into the turbine and the compressor. A bearing arrangement is disposed between the shaft and the bearing housing. The bearing arrangement including first and second bearings, each of the first and second bearings formed by a respective first and second plurality of roller elements engaged between a respective first and second inner race and a respective first and second outer race. The shaft is made of a steel alloy with a carbon content of less than 0.40% by weight.

Abstract: A bumper bearing assembly includes a bearing housing having a level of radial spring stiffness, wherein the bearing housing defines a bearing seat. A bumper bearing is connected to the bearing housing by a spring having a level of radial spring stiffness lower than that of the bearing housing. The bumper bearing is configured to apply the level of radial spring stiffness of the spring against a rotor with the bumper bearing spaced apart from the bearing seat. The bearing housing is configured to apply the level of radial spring stiffness of the bearing housing against the rotor with the bumper bearing seated against the bearing seat.

Abstract: A turbocharger including a turbine housing including a gas inlet passage and a turbine wheel arranged in the turbine housing. A bearing housing is connected to the turbine housing. A nozzle ring is disposed around the turbine wheel and a shroud is arranged in surrounding relation to at least a portion of the turbine wheel. The shroud is connected to the nozzle ring and the nozzle ring and shroud are connected to a heat shield. The heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing. The first passages and second passages are symmetrically arranged in a circular pattern about a rotational axis of the turbine.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: A working fluid (6) for a device (4) for converting heat into mechanical energy is disclosed. The working fluid (6) comprises a fluid (7) having a boiling temperature in the range between 30 and 250° C. at a pressure of 1 bar and nanoparticles (8) which are dispersed or suspended in the liquid phase of the fluid (7). Said nanoparticles (8) are instrumented as condensation and/or boiling nuclei and the surface of said nanoparticles (8) is adapted to support condensation and/or boiling.

Abstract: An embodiment of the present invention is a method of controlling an Organic Rankine Cycle system, the system comprising at least one feed pump (2), at least one heat exchanger (3), an expansion turbine (5) and a condenser (6), the organic Rankine Cycle comprising a feeding phase of an organic working fluid, a heating and vaporization phase of the same working fluid, an expansion and condensation phase of the same working fluid, wherein said method controls an adjusted variable (X), which is a function of an overheating of the organic fluid, by means of a controller (20) that acts by varying a control variable (Y), which is a parameter of the organic fluid in its liquid phase, and wherein the adjusted variable (X) is a temperature difference ([increment]T) between a current temperature of the organic fluid in vapor phase at the turbine inlet and a temperature threshold (Tlim), under which the expansion phase involves the formation of a liquid phase of the organic fluid.

Abstract: The invention relates to a thermal to energy conversion method and system using a Rankine cycle equipped with a heat pump, wherein heat pump (2) is integrated in the Rankine cycle.

Abstract: A system for regenerating energy in a vehicle. The system includes a Rankine loop having a heat exchanger and a preheater configured to pre-heat a Rankine working fluid prior to the Rankine working fluid being heated at the heat exchanger. The system also includes an engine coolant loop configured to direct engine coolant to and from the pre-heater, and an exhaust loop configured to direct engine exhaust to and from the heat exchanger.

Abstract: A rocker arm assembly for a valvetrain having a valve, a lash adjuster, and a camshaft lobe. The rocker arm assembly includes a shaft, a bearing rotatably supported by the shaft for engaging the lobe, and a rocker arm. The rocker arm has a pad for engaging the valve, and a socket for engaging the lash adjuster. A pair of walls are disposed between the pad and socket and define a valley for accommodating the shaft. A pair of upwardly-opening arc-shaped bearing surfaces are disposed longitudinally between the pad and the socket and are spaced laterally from each other. The bearing surfaces rotatably support the shaft when the bearing engages the lobe. A pair of retention elements extend from the walls into the valley above the bearing surfaces such that the shaft is prevented from moving out of the valley in absence of engagement between the bearing and the lobe.

Abstract: An apparatus includes a valve and an actuator. The valve has a portion movably disposed within a valve pocket defined by a cylinder head of an engine. The valve is configured to move relative to the cylinder head a distance between a closed position and an opened position. The portion of the valve defines a flow opening that is in fluid communication with a cylinder of an engine when the valve is in the opened position. The actuator is configured to selectively vary the distance between the closed position and the opened position.

Abstract: An exhaust valve includes a stem extending to a valve end. The valve end includes a pressure relief apparatus. An engine assembly includes a casing defining a cylinder bore, a combustion chamber and an exhaust passage. The combustion chamber is disposed between the exhaust passage and the cylinder bore. The engine assembly also includes a piston movable in the cylinder bore. The engine assembly further includes an exhaust valve movable between a first position blocking fluid communication through the exhaust passage and a second position allowing fluid communication through the exhaust passage. The exhaust valve includes a pressure relief apparatus configured to allow fluid communication through the exhaust valve from the cylinder bore to the exhaust passage when the exhaust valve is in the first position and a predetermined pressure threshold occurs in the cylinder bore between the exhaust valve and the piston.

Abstract: The present invention relates to an adjusting element for the axial displacement of a camshaft, supported displaceably along an axis of the camshaft, or a camshaft section arranged displaceably on a shaft along the axis of the camshaft, with the adjusting element being mobile between a first position and a second position, the adjusting element showing a guide section by which one or more projections of a camshaft, supported in an axially displaceable fashion, or a camshaft section, supported in an axially displaceable fashion, can cooperate in the first position such that the camshaft or the camshaft section can be axially displaced by a rotation about the axis of the camshaft, and the projection does not cooperate with the guide section in the second position. Furthermore, the invention relates to a device which comprises an axially displaceable camshaft, which shows one or more projections and such an adjusting element.