Abstract: A method moves a tube wave reflector in a well, generates a tube wave, receives a reflection, and determines the depth of one or more reflector locations from the elapsed time. Also, a method to locate a feature in a well deploys a bottom hole assembly (BHA), generates acoustic noise from the BHA, and autocorrelates to determine the BHA depth. Also, a system has a coiled tubing string to a BHA, a surface wave generator, a surface and/or distributed receiver, and a recorder to determine elapsed times between generation and receipt.

Abstract: A system and method for assembling a communication system in a drilling system configured to drill a borehole in an earthen formation. The communication system has a first antenna assembly and a second antenna assembly that are communicatively coupled together. The method includes attaching a first antenna to the first drill string component and attaching a second antenna to a second antenna assembly. The communication system is configured such that the first drill string component and the second drill string component are communicatively coupled together.

Abstract: In some aspects, an acoustic analysis system includes an acoustic source and a laser vibrometer. In some instances, the acoustic source can generate an acoustic signal in a wellbore defined in a subterranean region, and the laser vibrometer can detect movement of a surface in the wellbore in response to the acoustic signal. The detected movement can be analyzed, for example, to identify properties of materials in the subterranean region.

Abstract: A system and process for determining system operational characteristics of a drill string or completed well includes one or more detectors positioned along a fluid flow path in a wellbore. The detectors are operable to detect the presence of one or more transmitters circulated within the fluid flow path and to receive and record data based on detecting the transmitters. The system determines an operational characteristic, such as cutting sample identification information, flow rate, pump efficiency, lag, the presence of a washout, losses, or an equipment malfunction based on the data received and recorded by the detectors.

Abstract: It is described a method and a system for wireless in-situ sampling of a reservoir fluid from a hydrocarbon reservoir comprising obtaining a number of local samples of the reservoir fluid from different zones of the reservoir at given times. Local characterization of production fluid is obtained based on identifying chemical fingerprints of each of the number of local samples. This information can be used to determine local production rates from different zones in the well or from coming led wells.

Abstract: A vane pump is disclosed that includes a plurality of vanes and radial slots configured to provide a gap between the vane and the radial slot such that the vane has a different angular position relative to the direction of rotation in a radially extended position compared to an angular position in a radially-retracted position. The different angular positions provide different orientation of the arcuate surface of the vane tip portion with respect to the cam body inner surface, thus providing different fluid stop points on the vane tip portion arcuate surface.

Abstract: A component for a turbocharger can include a shaft made of a first material where the shaft includes a turbine wheel end and a shaft axis; a turbine wheel made of a second material where the turbine wheel includes a shaft end and a turbine wheel axis; a weld joint formed by solidification of at least a portion of a weld pool that includes the first material and the second material, where the weld joint joins the turbine wheel end of the shaft and the shaft end of the turbine wheel and where the weld joint includes an inner radial border and an outer radial border; a reservoir disposed radially inwardly of the inner radial border of the weld joint; and a solidified portion of the weld pool disposed in the reservoir. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable balloon in fluid communication with the distal end of the elongate reservoir. An actuator is provided for forcing the hardenable material from the elongate reservoir to inflate the inflatable balloon with hardenable material within the groove on the rotor disk. A sealing device for sealing the inflated inflatable element to form the balancing weight is also provided.

Abstract: An airfoil array includes a plurality of airfoils that differ in geometry over a plurality of geometry classes. An airfoil can include an airfoil body that has a first distinct piece and a second distinct piece that seats together with the first distinct piece. The first distinct piece and the second distinct piece include a mistake-proof feature configured such that the second distinct piece fully seats with the first distinct piece.

Abstract: Disclosed is a ceramic matrix composite (CMC) material including rare earth phosphate ceramic fibers embedded in a ceramic matrix, wherein the ceramic matrix also optionally includes a rare earth phosphate material. Methods for manufacturing the CMC material and gas turbine engine components formed of the CMC material are also disclosed.

Abstract: The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

Abstract: A method and device for manufacturing turbine blades (5; 7; 28; 33) made of a metal alloy. Starting with aluminum and titanium alloy bar (10; 34) having a simple and/or axisymmetric shape, at least two mutually interlocking blanks (2; 3; 4; 8; 11) are produced in the bar (10; 34) by waterjet cutting (16) and then each one of the blanks (2; 3; 4; 8; 11) thus obtained is machined separately in order to obtain the blades (5; 7; 28; 33) having a final profile.

Abstract: A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge, a trailing edge, a suction side extending from the leading edge to the trailing edge, and a pressure side extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating applied to the airfoil pressure side such that an uncoated margin is defined on the pressure side at the trailing edge.

Abstract: In some examples, an article may include a substrate and a coating on the substrate. The substrate may include a superalloy, a ceramic, or a ceramic matrix composite. The coating may include a first set of layers and a second set of layers. At least one layer of the first set of layers is between two layers of the second set of layers. The at least one layer of the first set of layers comprises one of amorphous silica or silicon nitride, and the at least two layers of the second set of layers comprises the other of amorphous silica or silicon nitride.

Abstract: A method for mounting rotor blades on a rotor disk along a predetermined pitch circle diameter in such a way that adjacent rotor blades, when properly mounted on the rotor disk and in the cold state, are clamped against each other with a predetermined preload. A clamping device which performs such a method has a plurality of clamping elements which are arranged in a uniformly distributed manner around a central axis, the number of which corresponds to the number of rotor blades to be mounted on the rotor disk and which in each case are designed for the locating of a rotor blade, wherein the clamping elements are moveable radially, exerting a radially inwardly directed force.

Abstract: A diffuser for a gas turbine including a support structure and a liner connected by holders. The liner includes a plurality of adjacent segments with overlapping borders. The overlapping borders are clamped to one another and slidingly rest one above the other.

Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Abstract: A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.

Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Abstract: The invention proposes an assembly (1) comprising: an exhaust casing (20), rotating about an axis (X-X), comprising a flange (23) for attachment to a mounting (42); a sealing plate (30) for rotation about the axis, the plate being added to the attachment flange of the casing and having a radial section comprising: a radially inner end portion (32), a radially outer end portion (34), and a bend (31) extending between the two end portions, said portions forming therebetween an angle of 80 to 100 degrees, the outer end portion having a length in an axial direction (L34) equal to 15% to 35% of the height (H) of the plate measured in the radial direction around the rotation axis, the outer end portion extending parallel to said axis, and said bend being open in the downstream direction relative to the flow of air.

Abstract: The present application provides seal assemblies having improved flexibility for reducing leakages between adjacent misaligned components of turbomachinery. The seal assemblies include a first outer shim formed of a flexible permeable material and a second outer shim formed of a substantially impervious material. At least the second outer shim is configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the first and second outer shims. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to meet operating requirements associated with turbomachinery. A turbomachine including the seal assembly is provided.

Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: Various methods and systems are provided for controlling a tip clearance between a shroud and blade of a turbocharger turbine. In one embodiment, a method for an engine including a turbocharger comprises, selectively adjusting a flow of coolant from one or more engine coolant sources through a shroud of a turbine based on a tip clearance between the shroud and a blade of the turbine.

Abstract: A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.

Abstract: A method of mixing airflow within an inner diameter (ID) mixing chamber of a turbine exhaust case (TEC) includes directing pressurized airflow into the ID mixing chamber. Cooling airflow is directed radially inward via a tube and is then expelled into the ID mixing chamber in a circumferential direction for mixing with the pressurized airflow.

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

Abstract: An exemplary gas turbine engine includes a radially stacked intershaft bearing assembly. The assembly includes an outer stubshaft having outer and inner diameter surface portions disposed concentrically with respect to one another. The outer diameter surface portion is rotatably connected to a body of the engine, and the inner diameter surface portion is rotatably connected to an inner stubshaft of the engine, so as to provide a stacked configuration of the inner stubshaft, the outer stubshaft, and the body along a radial direction orthogonal to a longitudinal axis of the engine.

Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.

Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.

Abstract: A support assembly supports a gas turbine in a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, where the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate attachable to the turbine casing interface includes a pin aperture that is sized to fit over the turbine casing pin in the slot.

Abstract: An arrangement to minimize vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a projection coupled to an inner cylindrical surface or the outer cylindrical surface of a fluid flow path of the gas turbine exhaust diffuser. The projection minimizes pressure oscillations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the second tangential strut is reduced. A method to minimize pressure oscillations in a gas turbine diffuser is also provided.

Abstract: In some implementations, there is provided an apparatus. The apparatus may include a first steam engine, an intermediate storage, and a second steam engine. The first steam engine may include a first inlet and a first exhaust, wherein the first inlet receives steam from a source of thermal energy. The intermediate storage may be coupled to the first exhaust, wherein the intermediate storage stores thermal energy provided by steam from the first exhaust. The second steam engine may include a second inlet coupled to the intermediate storage. Moreover, at least one of the first steam engine and the second steam engine may produce work. Furthermore, the first steam engine may be driven by the steam received from the source of thermal energy, and the second steam engine may be driven by steam from at least one of the intermediate storage and the first exhaust. Related apparatus and methods are also described.

Abstract: Disclosed is a heat energy recovery system including: a heat energy recovery circuit that causes a working medium to circulate by means of a circulation pump to exchange heat with supercharged air from a supercharger via a first heater and exchange heat with steam from an exhaust-gas economizer via a second heater, in order to integrally drive a turbine and a generator; and a controller that performs stop control to stop the circulation pump based on the flow state of the steam in a first steam flow path that causes the steam to flow from the exhaust-gas economizer to a soot blower.

Abstract: A camshaft is equipped with an inner shaft which is arranged rotatably inside a cylindrical outer shaft. Further, in the inner shaft, a plurality of pin holes extend along diametrical directions thereof, and are disposed at intervals along the axial direction of the inner shaft. The directions in which adjacent pin holes extend are arranged at angles obtained by dividing 360 degrees by the number of cylinders. The inner shaft and the inner cams are fixed in a state in which large diameter portions of pins, each of which is provided with a small diameter portion and a large diameter portion, are press-fitted through insertion holes of the inner cams and notches of the outer shaft, and are press-fitted into the pin holes.

Abstract: A roller tappet includes a housing, and the housing includes a first housing element and a second housing element. The first housing element has a receiving region configured to receive a roller of the roller tappet, and the second housing element is separate from the first housing element and is forged. The first housing element may be formed from metal sheet.

Abstract: An object is to provide a roller lifter which can maintain a proper dimensional accuracy of an outer diameter. A shaft (25) rotatably supporting a roller (30) is inserted through a pair of opposed portions (21) and swaged to be fixed. A cylindrical portion (61) is disposed to be fixed at a relative position to the opposed portions (21). Upon rotation of a cam (90), the cylindrical portion (61) is reciprocated via the roller (30). The roller lifter (10) includes a first member (20) in which the shaft (25) is swaged to be fixed to the opposed portions (21) and a second member (60) separate from the first member (20) and couplable via a coupling member to the first member (20). The second member (60) includes at least the cylindrical portion (61).

Abstract: The invention relates to an improved system of electro-mechanical hydraulic valve lifters for piston engine automobiles that increases fuel economy and reduces fuel emissions. The electro-mechanical hydraulic valve lifters enclose a magnetorheological fluid chamber, containing magnetorheological fluid. A control module manages voltage sent to the magnetorheological fluid in the magnetorheological fluid chamber. The control module introduces various amounts of magnetic flux to the magnetorheological fluid in the magnetorheological fluid chamber. The magnetorheological fluid's viscosity changes based on the amount of magnetic flux applied to it from the electromagnets and, along with the magnetorheological fluid chamber spring, controls how much an intake and exhaust port of the spark plug engine opens to control the amount of fuel used and exhaust let out of the engine.

Abstract: When a variable valve timing device controls an oil pressure control valve in a manner that a VCT phase is locked at a middle lock phase, an advance chamber and a retard chamber are made to communicate with each other, so that oil is filled into both of the advance chamber and the retard chamber when the oil pressure control valve supplies oil to one of the advance chamber and the retard chamber in an oil filling mode. An oil pump supplies oil to the oil pressure control valve, and is controlled to have an oil flow rate that is equal to or larger than a predetermined value in the oil filling mode.

Abstract: An apparatus for measuring at least one of temperature and pressure within a cylinder of an internal combustion engine can include an engine valve and a sensor. The internal combustion engine can include a valvetrain having rocker arm assembly, a camshaft, a valve, and a hydraulic lash adjuster. The engine valve can have a valve head and a valve stem extending from the valve head in an axial direction. The valve head can have a valve face configured to be in pressure communication with an engine cylinder. The valve stem can have an outer surface with a cylindrical portion and a variably-shaped portion. The variably-shaped portion can define a target detectable by the sensor and the sensor can be installed adjacent to the target. Alternatively, the sensor can be positioned to detect a level of force at some point along the valvetrain.

Abstract: A valve train device for an engine includes: a shaft portion; a cam element portion which is mounted on the shaft portion; and an operation member. The cam element portion includes a first end surface cam and a second end surface cam. Each of the first end surface cam and the second end surface cam includes a lift portion. The operation member includes a first operation member and a second operation member. The first operation member causes the cam element portion to move in a first direction, and the second operation member causes the cam element portion to move in a second direction. The first end surface cam includes a first slope portion, and guides the first operation member radially outwardly; and a displacement allowing portion which is formed adjacent to the first slope portion, and allows relative displacement between the first operation member, and the cam element portion.

Abstract: A camshaft for a multiple-cylinder internal combustion engine may include a sliding element comprising at least two cam elements, as well as a splined shaft that extends in an axial direction and on which the sliding element is received. The sliding element may comprise an internal spline system that interacts with an external spline system of the splined shaft such that the sliding element is seated fixedly on the splined shaft so as to rotate with the splined shaft. The sliding element may be received on the splined shaft such that the sliding element can, at least initially, be displaced axially. For axially-fixing the sliding element to the splined shaft, the sliding element may include a positively locking connection that is configured in the axial direction and is produced by way of at least one calked connection between the sliding element and the splined shaft. It should be understood that many camshafts include more than one sliding element.

Abstract: In a variable valve mechanism of an internal combustion engine, when a slider is displaced relative to an input member and an output member in an axial direction, the output member turns relative to the input member in a swing direction, whereby a lift of a valve is increased or reduced. The variable valve mechanism is brought into a lift retaining state when the slider is placed in an idle running range located on a reducing direction side with respect to a boundary position. The lift retaining state is a state where when the slider is displaced in the axial direction, the input member and the output member are displaced together with the slider in the axial direction, so that the relative displacement of the slider and the relative turning of the output member do not occur and the lift of the valve is retained.

Abstract: An oil cooler for a vehicle includes an inflow tank through which a working fluid flows in. An outflow tank is spaced apart from the inflow tank by a predetermined interval and has a discharge hole at one side which faces the inflow tank. A plurality of tubes connect the inflow tank with the outflow tank longitudinally such that the working fluid flows therethrough. A bypass valve is integrally mounted at an outer side of the one end portion of the inflow tank and connected to an inner side of the inflow tank to bypass or flow the working fluid flowed therein into the inflow tank by selectively opening and closing according to a temperature of the working fluid. An outflow pipe has one end mounted to the discharge hole and another end thereof mounted to the bypass valve to connect the outflow tank with the bypass valve.

Abstract: Aspects of the disclosure are directed to a shaft configured with a first hole, a bearing race coupled to the shaft and configured with a second hole and a third hole, and an oil scoop configured to receive oil and provide the oil to the shaft, where the first and second holes are oriented axially with respect to the shaft, and where the third hole is oriented radially with respect to the shaft. In some embodiments, a second oil scoop is configured to receive oil and provide the oil to the shall. The oil scoop and the second oil scoop may be concentric with respect to one another.

Abstract: A vehicle exhaust system includes an exhaust component having an outer surface and an inner surface that defines an internal exhaust component cavity. At least one hole is formed in the exhaust component to extend through a wall of the exhaust component from the outer surface to the inner surface. A member is formed from a resistive material and is configured to overlap the at least one hole. At least one spacer is configured to space the member away from the inner or outer surface of the exhaust component to create an open cavity between the member and the exhaust component. In one example, an actuator is configured to cover and uncover the member dependent upon an operating characteristic to vary damping.