Abstract: A system includes a regional blending facility having a number of bulk receiving facilities, where each bulk facility receives and stores a particle type having a distinct size modality, a bulk moving device that transfers particles between the bulk receiving facilities and of a blending/continuously receiving vessel and/or a mixer, and a carrying medium vessel. The mixer receives particles from the blending/continuously receiving vessel and/or the bulk moving device, receives a carrying medium from the carrying medium vessel, mixes the particles with the carrying medium, and provides a mixed treatment fluid. The system includes a fluid conduit that fluidly couples a wellsite location with the regional blending facility, where the fluid conduit delivers the mixed treatment fluid to the wellsite and/or delivers produced fluid from a wellbore positioned at the wellsite to the regional blending facility.

Abstract: A method of injecting well treatment fluid including proppant and proppant-spacing filler material through a wellbore into the fracture, heterogeneously placing the proppant in the fracture in a plurality of proppant clusters or islands spaced apart by the material, and removing the filler material to form open channels around the pillars for fluid flow from the formation through the fracture toward the wellbore. The proppant and channelant can be segregated within the well treatment fluid, or segregated during placement in the fracture. The filler material can be dissolvable particles, initially acting as a filler material during placement of the proppant in the fracture, and later dissolving to leave the flow channels between the proppant pillars. The well treatment fluid can include extrametrical materials to provide reinforcement and consolidation of the proppant and/or to inhibit settling of the proppant.

Abstract: A method of fracturing a reservoir comprising the steps of pumping a geopolymer precursor fluid through a wellbore into the reservoir at a fracture pressure, the geopolymer precursor fluid at the fracture pressure generates fractures in the reservoir, wherein the geopolymer precursor fluid is comprised of an amount of aluminosilicate, an amount of alkaline reagent, and a permeability enhancer, allowing the geopolymer precursor fluid to fill the fractures in the reservoir, shutting-in the wellbore at a wellbore pressure, the wellbore pressure maintains the geopolymer precursor fluid in the fractures, allowing the geopolymer precursor fluid to harden for a hardening time to form a geopolymer in the fractures, the geopolymer has a geopolymer matrix, the geopolymer matrix has a permeability, the geopolymer has a compressive strength, and reducing the wellbore pressure allows a reservoir fluid to flow from the reservoir through the geopolymer matrix of the geopolymer to the wellbore.

Abstract: A method of controlling a downhole operation includes: deploying a work string into a wellbore, the work string comprising a deployment string and a bottomhole assembly (BHA); digitally marking a depth of the BHA; and using the digital mark to perform the downhole operation.

Abstract: Selecting hydrocarbon wells for workover. At least some of the illustrative embodiment including: calculating a plurality of present-performance index values for a respectively plurality of wells, each present-performance index value based on a well's performance with respect to the plurality of wells, and each present-performance index value dimensionless; calculating a plurality of future-performance index values for the respective plurality of wells, each future-performance index value based on a well's expected future performance with respect to the plurality of wells, and each future-performance index value dimensionless; combining a present-performance index value and a future-performance index value for a first well to create a first combination index; combining a present-performance index value and a future-performance index value for a second well to create a second combination index; selecting the hydrocarbon well based on the first and second combination indices.

Abstract: A method of pressure testing downhole tubular connections includes connecting a pressure monitoring device to a test port on a downhole connector of a downhole tool, connecting the pressure monitoring device to a reference port, pressurizing the test port and the reference port, and monitoring for a pressure difference between the test port and the reference port with the pressure monitoring device.

Abstract: A system and method for positioning a tool within a wellbore, wherein the interior surface of a positioning apparatus includes one or more pluralities of grooves, each defining a selected profile. A tool is lowered into the positioning apparatus, having a blade in communication therewith. The blade includes a plurality of protruding members, which define a profile complementary to at least one of the selected profiles formed by one of the pluralities of positioning apparatus grooves. A biasing member, in communication with the blade, can continually bias the blade toward the interior surface of the positioning apparatus to cause the profile of the blade to engage within the corresponding complementary profile of the positioning apparatus. Positioning a tool in this manner is advantageous for locating cutting tools at a precise location to sever a joint, perforate casing or stack multiple tool operations at a fixed, targeted point within a wellbore.

Abstract: An apparatus, method and computer-readable medium for locating a joint of a casing disposed in a borehole are disclosed. The apparatus includes a sensor oriented in a plane orthogonal to a longitudinal axis of the casing. The sensor measures a magnetic field induced in the casing by the earth's magnetic field. A tool conveys the sensor through the casing along a path that is radially offset from a longitudinal axis of the casing. Transverse magnetic field measurements are obtained by the sensor at a plurality of depths along the casing. A change in the transverse measurements is identified and used to determine the location of the casing joint.

Abstract: In one aspect, an apparatus for use in a wellbore is disclosed that may include a transmitter placed on an electrically-conductive member at a first location in the wellbore configured to induce electromagnetic waves that travel along an outside of the conduit and a receiver placed on the electrically-conductive member at a second distal location in the wellbore configured to detect the electromagnetic waves induced by the transmitter.

Abstract: A submersible electrical machine includes a first magnetic package spaced axially from a second magnetic package, a first stator displaced axially from the first magnetic package by a first air gap, a second stator displaced axially from the second magnetic package by a second air gap. The electrical machine can be operated as a generator or as a motor. When operating as a generator, a turbine can rotate the magnetic packages relative to the stators in response to fluid flowing axially across the electrical machine.

Abstract: A method and apparatus for downhole data transmission. The method comprising monitoring electrical impedance properties of a downhole formation by applying an electrical signal between a first portion and a second portion of a drill string that are electrically insulated from each other by an insulating portion, selecting a frequency for transmitting data by electromagnetic telemetry based at least in part on the monitored electrical impedance and transmitting the data by encoding the data in a waveform having the selected frequency and applying the waveform between the first portion and the second portion of the drill string.

Abstract: Methods and software tools for determining wellbore-strengthening information for a drilling operation, the method including inputting wellbore parameters into a wellbore simulator, importing wellbore-strengthening options into the wellbore simulator, and performing a plurality of wellbore simulations to obtain fracture information, wherein the performing the plurality of wellbore simulations includes selecting at least one of the wellbore parameters and determining the affect of the selected wellbore parameter on the wellbore. The method further includes selecting a wellbore-strengthening option based on the fracture information and outputting the selected wellbore-strengthening option.

Abstract: System and method for predicting the mud weight window in formations, particularly those formations having geologic structures such as salt domes. One embodiment is a computer-implemented method of modeling a formation in 3-D and determining a plurality of effective stress ratios for the modeled 3-D formation using finite element analysis. Thereafter, the trajectory of a proposed wellbore through the 3-D modeled formation is plotted and the specific effective stress ratios along the wellbore are selected to form a data set. The 3-D data set of effective stress ratios is then imported into 1-D modeling software and combined with 1-D data. The combined data is thereafter utilized to estimate the mud weight window for the formation around the wellbore.

Abstract: A method for revealing anomalous discontinuity interfaces in pore pressures in non-drilled geological formations and an implementing system.

Abstract: The present invention relates to ruggedized downhole tools and sensors, as well as uses thereof. In particular, these tools can operate under extreme conditions and, therefore, allow for real-time measurements in geothermal reservoirs or other potentially harsh environments. One exemplary sensor includes a ruggedized ion selective electrode (ISE) for detecting tracer concentrations in real-time. In one embodiment, the ISE includes a solid, non-conductive potting material and an ion selective material, which are disposed in a temperature-resistant electrode body. Other electrode configurations, tools, and methods are also described.

Abstract: A downhole fluid properties optical analysis probe (1) to analyze at least one property of a multiphase flow mixture (100) flowing in a hydrocarbon well (51) has an elongated cylindrical body shape and comprises an optical tip (5) at one end of the elongated cylindrical body arranged to be in contact with the multiphase flow mixture (100), and an optoelectronics module (11) at another end of the elongated cylindrical body arranged to be separated from the multiphase flow mixture (100) and coupled to the optical tip (5) by an optical fiber bundle.

Abstract: The present invention provides a device comprising: (a) a proximal end of the device comprises an inner first conduit within the lumen of an outer second conduit, (b) a distal end of the device comprises the outer second conduit in fluid communication with a third conduit and a fourth conduit through a Y-shaped, T-shaped or U-shaped junction, (c) the third conduit terminates in a triggering mechanism, and (d) the fourth conduit is in fluid communication through a one-way valve, wherein fluid can only convey in a direction from the fourth conduit towards the second outer conduit, with an aperture.

Abstract: A hydrocarbon sample is subjected to a chemically selective J-editing nuclear magnetic resonance (NMR) pulse sequence. Resulting signals are analyzed in order to identify a coupling frequency present in at least one molecule of the hydrocarbon sample. A J-coupling frequency of approximately 150 Hz is indicative of a component having an internal double bonded carbon atom (i.e., an olefin). The presence of an olefin in a hydrocarbon sample can be indicative of the presence of a synthetic based mud (SBM) in the sample.

Abstract: The present invention relates to a ground milling machine, in particular a road milling machine, a recycler, a stabilizer or a surface miner, comprising a milling drum with a milling drum width (a) extending along its rotational axis and with at least two chiseling devices, each of which comprises a chisel and a chisel holder, and a sensor device for determining wear on the at least two chiseling devices in a contactless manner, said sensor device comprising a sensor for measuring a wear parameter of the at least two chiseling devices, the sensor being movable at least over a part of the milling drum width (a) in order to set an identical measurement angle (?) and an identical position of the sensor relative to the at least two chiseling devices in order to measure the wear parameter of the at least two chiseling devices. The present invention further relates to a method for determining wear on the at least two chiseling devices of the ground milling machine in a contactless manner.

Abstract: A friction bolt including an elongated metal tube and a plurality of friction members. The metal tube includes interior and exterior surfaces, a tapered distal end portion, a proximal end portion, and a slit extending along a length of the elongated metal tube. The plurality of friction members extend outward from the exterior surface, and at least some of the friction members have an exposed planar portion to frictionally engage an inner surface of a bore within which the friction bolt is inserted.

Abstract: A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade.

Abstract: An apparatus includes a substrate having one or more fastener apertures that extend therethrough. Each fastener aperture has a centerline and includes first and second circular segmented regions and a central channeled region. Each circular segmented region has a diameter and a segment length that extends along the centerline, wherein the segment length is greater than one-half the diameter. The central channeled region extends along the centerline between the first and the second circular segmented regions. The central channeled region has a height that is less than the diameter of the first and the second circular segmented regions.

Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.

Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.

Abstract: The invention relates to a blade of an axial turbomachine comprising an airfoil which extends radially and a first set of branches or divisions, which radially extend a radial end of the airfoil, and a second set of branches which radially extend the other of the radial ends of the airfoil and which are offset over the circumference of the turbomachine. The branches extend axially along the entire length of the airfoil. The sets have different numbers of branches. The branches further occupy the channel of the turbomachine and further counteract debris in the event of intake.

Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.

Abstract: A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.

Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers (22) may be positioned within a pressure side nearwall cooling channel (48) and a suction side nearwall cooling channel (50) that are both in fluid communication with a trailing edge channel (30). The trailing edge channel (30) may also include cooling fluid flow controllers (22) extending between the outer walls (12, 13) forming the pressure and suction sides.

Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.

Abstract: A method of forming a structural connection between a spar cap 14 and an aerodynamic fairing 12. A composite comprising an uncured matrix and a compressible solid is applied between the spar cap and fairing and is then compressed and cured to adhere the fairing to the spar cap. The cured matrix composite has a void volume of at least 20%. The high void volume means that as the fairing is compressed into place and compresses the composite, it has space in which to deform so as not to place undue stress on the fairing and to produce a lightweight connection.

Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Abstract: A nozzle segment assembly for a gas turbine engine may generally include inner and outer ring support segments and a nozzle fairing positioned between the inner and outer ring support segments. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall and an inner endwall. In addition, the nozzle fairing may include a strut vane extending between the inner and outer endwalls. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.

Abstract: A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing.

Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.

Abstract: A turbine wheel for a turbine engine is provided. The turbine wheel includes a disk carrying blades including internal channels for passing a flow of cooling air, each blade having a platform carrying an airfoil and connected by a tang to a root. The blade roots are engaged in grooves in the periphery of the disk and their tangs define between them spaces for housing sealing and damping members, which cooperate with the inside faces of the platforms to define air flow cavities. The tangs of at least some of the blades include cooling air outlet orifices that open out both into internal channels in the blades and into the cavities.

Abstract: According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud.

Abstract: Shroud assemblies and shrouds for gas turbine engines are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a rib disposed between and in contact with the forward flange and the rear flange.

Abstract: The present disclosure is directed to a waste heat recovery system used in conjunction with a power source system. A pump may pressurize a working fluid to a set pressure threshold and feed the working fluid through a fluid flow path. An evaporator and a condenser may each connect to the fluid flow path. Connected to each the evaporator and the condenser may be a turbine able to receive the working fluid when the working fluid is above the set pressure threshold and a predetermined thermal threshold. An electric machine having a motor mode or a generator mode may then attach to the turbine. Attached to the other end of the turbine may be a shaft coupling also attached to the pump. The pump may be powered by the electric machine operating in a motor mode through the shaft coupling to provide pressure to the waste heat recovery system.

Abstract: A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more oxidant passages and one or more fuel passages. The distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is configured to measure a fuel flow rate for a respective fuel passage of the one or more fuel passages of the respective combustor based at least in part on a fuel pressure drop along the respective fuel passage.

Abstract: A dynamic system estimation device and method, whereby estimation for more performance parameters than there are sensors can be performed, the estimation taking temporal changes into account. The dynamic system estimation device includes: a prescribed number of sensors that detect prescribed observation values from a gas turbine engine; and a Kalman filter that uses a dynamic model of the gas turbine engine and estimates the state of the gas turbine engine, on the basis of the observation values detected by the sensors. The gas turbine engine includes an element having changes in temporal performance recorded by performance parameters. The Kalman filter enables more than the prescribed number of performance parameters to be estimated, as a result of introducing a first-order lag element in place of the element.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.

Abstract: An arrangement for a turbomachine is provided. The arrangement includes a vane for directing a hot gas during the operation of the turbomachine, a stator ring for securing the vane, a heat shield for protecting the stator ring from the hot gas flow wherein the heat shield is arranged in downstream direction of the hot gas flow in front of the stator ring characterized in that the heat shield comprises a plurality of channels formed therein for directing a cooling air.

Abstract: A turbomachine of this disclosure includes a rotation shaft, a first impeller, a first bearing, and a second bearing. The first impeller is fixed to the rotation shaft and includes a low-pressure-side surface. The first bearing is adjacent to the low-pressure-side surface of the first impeller and supports the rotation shaft. The second bearing is disposed on an opposite side of the first impeller from the first bearing and supports the rotation shaft. The rotation shaft includes a first tapered portion gradually increasing in diameter toward the first impeller. The first bearing includes a first support surface supporting the first tapered portion.

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Abstract: Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.

Abstract: A turbocharger turbine having a blade-gap zone between the blades and the shroud wall. The blade-gap zone is larger at and near the exducer than at an upstream location where the shroud wall is at its minimum radius. Also disclosed is a method of customizing and manufacturing a turbine by establishing an optimized blade-gap zone at the exducer, and machining it into a turbine housing.

Abstract: An actuator housing is provided. The actuator housing may comprise a body, and a first side of the body including a first pin interface and a first threaded hole clocked relative to the first pin interface. The first pin interface and the first threaded hole may be configured to interface with a solenoid housing. A second side of the body may be orthogonal to the first side. The second side may include a circular geometry with a cylindrical member disposed central to the circular geometry. A toggle assembly interface may be recessed in the second side and disposed within the cylindrical member.

Abstract: A turbine engine fan rotor having a disk carrying blades, a substantially frustoconical cover mounted on the disk, and axial retention device for retaining the blades and including a ring mounted in an annular groove in the disk and forming a bearing surface for roots of the blades. The ring is festooned or crenellated and co-operates with a festooned radial annular lip of the disk. The rotor also has at least one axial tooth inserted in hollow portions of the ring and of the lip of the disk. Two coaxial parts arranged radially inside the disk have respective first and second fastener flanges for fastening to the disk, said flanges being axially interposed between the cover and the disk, being circumferentially offset relative to one another, and being fastened independently of one another to the disk.

Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.