Abstract: Apparatus and associated methods relate to a decline curve analysis method for predicting oil and gas production from an oil well, where a prediction curve for oil and/or gas data transitions from a first characteristic function to a second characteristic function at the bubble point. In an illustrative example, the first and second characteristic functions may be of the monotonically decreasing type. A distinction between the two characteristic functions may be that the absolute value of the decline for the second characteristic function is greater than or equal to the absolute value of the decline of the first characteristic function for each value of time and/or cumulative oil/gas past the bubble point. In various embodiments, the method may give more accurate predictions for oil and/or gas production once the stimulated reservoir volume reaches the bubble point.

Abstract: In a method of gravel packing a wellbore in a subterranean formation, the wellbore having a cased section and an uncased section, the method may include pumping into the wellbore a gravel pack composition having gravel and a carrier fluid, where the carrier fluid includes an oleaginous fluid and an inorganic solid aggregator material.

Abstract: A system includes an inner string assembly disposed within an outer casing. The inner string assembly includes a seal member in sealing engagement with the outer casing. An expansion sleeve is coupled to an end of the outer casing. An expandable liner is coupled to the expansion sleeve. A cone assembly is coupled to the inner string assembly and positioned proximate to the expansion sleeve when the inner string is in a running position.

Abstract: A method of optimizing the operation of a gas lift well including the steps of: collecting data from at least one surface mounted sensor, the at least one surface mounted sensor including a skin-mounted temperature sensor, the at least one surface mounted sensor mounted to the gas lift well's surface equipment; collecting ambient temperature data; and determining gas lift performance from data so obtained. A system and field test kits for optimizing the operation of a gas lift well.

Abstract: The present invention relates to a system for facilitating the extraction of hydrocarbons, in particular extraction by RF heating of high-viscosity hydrocarbons in situ by means of an antenna comprising a coaxial array of mode converters.

Abstract: The invention provides formulations for facilitating the removal of oil from a surface using a chisel composition, wherein the chisel composition includes a polymer having one or more binding points with a high affinity for the surface, and one or more hydrophilic segments that form a hydrophilic coating on the surface, rendering the surface water-wet and thereby facilitating the removal of oil from the surface. The invention also provides for methods of use of such formulations.

Abstract: The production of hydrocarbons from a hydrocarbon bearing formation is enhanced by introduction into the formation a non-aqueous fluid containing a liquefied natural gas.

Abstract: A method, system, and electrode assembly are disclosed that maximizes the lifetime of electrodes for high energy electrical discharges in water by arranging the electrodes in concentric rings or a stack of concentric rings. The radii and the thickness of the ring electrodes are optimized for electrical reliability, low jitter, and minimal erosion. In one embodiment, the electrode assembly is configured to be disposed in a subterranean dielectric medium, receive an electric current pulse having a length of time greater than 100 microseconds, and form an electric arc between the first electrode and the second electrode, thereby producing a pressure pulse axially away from the insulator.

Abstract: The disclosure provides fracturing methods having advantage over current fracturing methods. The disclosed fracturing methods can change the fracture gradient of the downhole subterranean formation. For example, one or more of the fracture gradients of the low and high stress zones of the downhole subterranean formation can be changed. Furthermore, in relation to current practices, the methods can decrease the extent and/or degree of fracturing within low stress downhole formations and increase the degree of fracturing within high stress formations.

Abstract: Methods including preparing a silanization composition comprising an aqueous base fluid and an alkyltrialkoxysilane; coating the silanization composition at least partially onto proppant particulates, thereby forming coated proppant particulates, wherein the silanization composition imparts hydrophobicity to the proppant particulates; and introducing the coated proppant particulates into a subterranean formation. The alkyltrialkoxysilane in the silanization composition may have the formula R1(OR2)3Si, where R1 is a C8 to C22 alkyl chain and R2 is an alkyl group selected from the group consisting of methyl, ethyl, butyl, tert-butyl, isopropyl, and any combination thereof.

Abstract: Injection fluids formed of reverse emulsions and related methods of forming and using reverse emulsions for cavity control in solution mining. The reverse emulsion can reduce the volume of oil required to create an oil pad at the roof of a solution mining cavern in order to prevent vertical leaching and cavern collapse. The reverse emulsion can be formed from an emulsifier, a brine solution and oil. The emulsifier concentration can range from about 1% to about 5% by weight of the reverse emulsion. The emulsifier and the oil can be combined to form an oil/emulsifier mixture, wherein the oil/emulsifier mixture is combined with the brine solution to form the reverse emulsion. The oil/emulsifier mixture can be from about 1% to about 5% by weight of the reverse emulsion.

Abstract: In one embodiments, a method includes drilling a wellbore in a formation with a drilling tool. The method further includes receiving electromagnetic radiation using an opto-analytical device coupled to the drilling tool. The method also includes determining torsion associated with drilling the wellbore based on the received electromagnetic radiation.

Abstract: A laser alignment device for a drill rig having an elongate drill rod, the laser alignment device including a head unit having at least a pair of laser emitting devices mounted independently to one another thereon, each of the laser devices movable in one plane only and oriented in substantially opposite directions to one another, an attachment means to attach the head unit to a drill rig and a length adjustable assembly to adjust the separation distance between the head unit and the drill rod, wherein the alignment device is used to align at least the azimuth of the drill rod relative to survey marks.

Abstract: In one aspect, a method of optimizing a sequenced hydraulic fracturing treatment to be performed on a well includes predicting, based on a well model of the well and a hydraulic fracturing treatment schedule, a seal state of a perforation cluster. The method may further include updating, based on the predicted seal state, a pilling operation of a stage of the hydraulic fracturing treatment schedule. The method may further include modifying the sequenced hydraulic fracturing treatment schedule to be performed based on the updated pilling operation. The well model includes a geomechanical model of the well and a geological formation.

Abstract: In one embodiment, a method includes drilling a wellbore in a formation with a drilling tool. The method further includes receiving electromagnetic radiation using an opto-analytical device coupled to the drilling tool. The method also includes determining a distance between a portion of the drilling tool and the formation based on the received electromagnetic radiation.

Abstract: A method for equitable allocation of hydrocarbon component yields which uses the output of process modeling of the hydrocarbon processing system with the individual source streams commingled into a single inlet stream to create a differential value table which can be used to provide the allocation of output product to the individual source streams that are accountable for the individual component yield.

Abstract: A flow meter for measuring multi-phase flow and method of use comprising an impeller assembly having a one or more blades in an asymmetric blade configuration on a rotational shaft and one or more sensors to measure partial rotations of the blades. Sensors may obtain impeller rotational information associated with various portions of the flow stream. With this multi-phase fluid flow may be determined from the determined local velocity information, the operation of a fluid-flow system may be enhanced.

Abstract: A method of initiating a process in a downhole tool includes connecting a downhole tool to an initiator device that contains wires capable of creating a loopback and/or loaded condition when a closed connection is made. The initiator device is further capable of indicating successful initiation.

Abstract: A downhole tool is conveyed within a borehole extending into a subterranean formation. Fluid is drawn from the subterranean formation into the downhole tool, wherein the fluid comprises heavy oil. Fluorescence intensity of the drawn fluid is measured via a sensor of the downhole tool, and asphaltene content of the drawn fluid is estimated based on the measured fluorescence intensity.

Abstract: Systems and methods for monitoring and characterizing well bores, subterranean formations, and/or fluids in a subterranean formation using well evaluation pills are provided. In one embodiment, the methods comprise: introducing a well evaluation pill into a portion of a well bore penetrating a portion of a subterranean formation; allowing the well evaluation pill to interact with one or more components in the portion of the subterranean formation; detecting a change in the composition or properties of the well evaluation pill; and determining the presence of one or more components in the portion of the subterranean formation based at least in part on the detected change in the composition or properties of the well evaluation pill.

Abstract: Disclosed is a monitoring probe for observing groundwater, which is put into an observation well for observing the groundwater to indicate a position of a fresh water-salt water interface of the groundwater. According to the present invention, both ends of a probe body are separated from an inner circumference of an observation well by a catch preventing portion having a convex curved portion or a dumbbell-shaped portion, so that the probe body can be smoothly moved up and down without being caught by a ground-water inlet port of the observation well, thus providing an exact position of a fresh water-salt water interface.

Abstract: A downhole sensor package for detecting one or more thermophysical properties of a downhole fluid, comprising a sensor housing having a fluid input port and a fluid output port; an inner flow tube located within and axially defined with the sensor package housing; an outer flow annulus defined between the inner flow tube and the sensor housing, wherein the inner flow tube is in fluid communication with the outer flow annulus; and a vibration source and a vibration detector engaging the inner flow tube; and methods for using the same are disclosed.

Abstract: A method and system for applying a liner material to a contoured surface, such as an exposed rock face in an underground hard rock mine, is disclosed. Locations of a plurality of spatially distributed surface grid points on the contoured surface may be detected so as to generate a representative topographical profile of the contoured surface. Based on the plurality of surface grid points, a spray path for a liner application device configured to emit a spray of the liner material may be determined. In some cases, the spray path may have a trajectory that follows the topographical profile of the contoured surface offset therefrom within a spray range of the liner application device. Liner material may then be sprayed onto the contoured surface while controlling the liner application device to undertake at least one pass of the spray path.

Abstract: Geocomposite articles that can provide a barrier against high conductivity water e.g., ocean water, are described and their method of manufacture, for waterproofing surfaces that contact high conductivity water. The geocomposite article mat includes a woven or non-woven geotextile sheet or mat containing a powdered or granular partially cross-linked acrylamide/acrylate/acrylic acid copolymer across its entire major surface(s). The powdered or granular copolymer has an unexpectedly high free-swell when hydrated with High Conductivity water, such as ocean water. A liquid-impermeable cover sheet is adhered to the upper major surfaces of the filled copolymer-carrying geotextile to provide a primary high conductivity water barrier layer that, if ruptured, is sealed by the swell of an underlying layer of water-insoluble, partially cross-linked acrylamide/acrylic acid copolymer.

Abstract: A transportation main roadway and stope branch roadways are arranged by adopting a wangeviry coal mining method. A plurality of stope branch roadways are divided into multiple mining stages, based on which the stope branch roadways are skip-mined; and coal pillars are not reserved among the stope branch roadways. The transportation main roadway is a main transportation channel, and the stope branch roadways are coal mining roadways. All the stope branch roadways are sequentially stoped in a skip-mining manner according to the designed mining sequence and are sequentially and timely filled. The coal never stoped or the filled stope branch roadways is/are used as supports for controlling roofs at the two sides of the stope branch roadways, and the stope branch roadways are sequentially stoped according to a plurality of mining stages, and finally the coal pillar-free mining is realized.

Abstract: A device usable as an impeller has a plurality of vanes rotating eccentrically about a shaft. Eccentric rotation is enabled by a cam mounted on the shaft. The vanes are received within slots in a rotor which surrounds the shaft and rotates about an axis coaxial with the shaft. The rotor rotates within a housing having a cylindrical surface facing the rotor. The surface is eccentric to the shaft. The vanes execute reciprocal motion upon rotation of the rotor. The vane motion is constrained so that the edges of the vanes remain proximate to the cylindrical surface during rotation.

Abstract: A gas turbine engine includes first and second shaft members in an interference fit relationship with one another at an interface. The first and second shaft members respectively include first and second flanges that are arranged adjacent to the interface. The first and second flanges respectively include first and second threads that are configured to cooperate with a tool during disassembly of the first and second shaft members.

Abstract: A torque converter turbine is provided. The torque converter turbine includes a plurality of blades, an annular bowl shaped blade supporting portion supporting the blades and a mass fixed to the blade supporting portion. A method of forming a torque converter turbine is also provided. The method includes providing a blade supporting portion of a turbine shell with mass and connecting a plurality of blades to the blade supporting portion.

Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.

Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).

Abstract: The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade.

Abstract: An additive manufacturing system utilizing an epitaxy process, and method of manufacture, utilizes a heating source and a cooling source to control thermal gradients and a solidification rate of each slice of a workpiece manufactured from a seed having a directional grain microstructure. An energy gun is utilized to melt selected regions of each successive layer of a plurality layers of a powder in a powder bed to successively form each solidified slice of the workpiece.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.

Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.

Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections coupled at a turn section. A baffle includes a body arranged in the second passage section to define two cooling flow paths, and a first wedge region extends from the body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the two cooling flow paths.

Abstract: A turbine assembly is provided having a hollow aerofoil having a cavity with an impingement tube insertable inside the cavity and used for impingement cooling of an inner surface of the cavity, and a platform arranged at a radial end of the hollow aerofoil, and a cooling chamber used for cooling of the platform which is arranged relative to the hollow aerofoil on an opposed side of the platform. The cooling chamber is limited at a first radial end from the platform and at an opposed radial second end from a cover plate. The impingement tube is formed from a leading piece and a trailing piece. The leading piece extends in span wise direction at least completely through the cooling chamber from the platform to the cover plate and the trailing piece terminates in span wise direction at the platform.

Abstract: The invention relates to a carrier ring for a high-pressure gas turbine of a gas turbine plant, which has a high-pressure combustion chamber upstream of the high-pressure gas turbine, a compressor upstream of the high-pressure combustion chamber, a low-pressure combustion chamber downstream of the high-pressure gas turbine, a low-pressure gas turbine downstream of the low-pressure combustion chamber, and a rotor that carries rotor blades for the compressor, for the high-pressure gas turbine, and for the low-pressure gas turbine. The carrier ring carries guide blades and/or heat shields of the high-pressure gas turbine and can be fastened to the high-pressure combustion chamber. The installation of the carrier ring can be simplified by segmenting the carrier ring at least in the area of the guide blades thereof and/or of the heat shields thereof in the circumferential direction, wherein the segmented carrier ring has at least two ring segments that carry the guide blades and/or the heat shields.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.

Abstract: Provided is a turbine including a rotor wheel including a plurality of dovetail grooves and a insertion groove, the insertion groove including a first catching groove; a plurality of first buckets, each of the plurality of first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to the dovetail groove; a second bucket including a vane, a platform provided at a first end portion of the vane, and a protrusion portion and configured to be inserted into the insertion groove, the protrusion portion including a second catching groove; and a fixing member configured to be inserted into each of the first and second catching grooves, the fixing member configured to restrict radial movement of the second bucket.

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier.

Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.

Abstract: A transmission mechanism includes a planet gear, a set of sun gear teeth and a set of ring gear teeth. The planet gear is configured to be mounted to a synchronization ring for rotation relative to the synchronization ring about a planet gear axis. The set of sun gear teeth are meshed with teeth of the planet gear. The set of sun gear teeth is configured to rotate and drive motion of the planet gear in a circumferential direction about an axis of the set of sun gear teeth. The set of ring gear teeth are meshed with the teeth of the planet gear. The set of sun gear teeth and the set of ring gear teeth are spaced apart from one another.

Abstract: A gas turbine engine variable guide vane has a fixed portion on an upstream side, a movable flap on a downstream side and a transfer slot between a fixed portion trailing surface and a movable flap leading surface. The movable flap has opposite pressure and suction sides along a chord line between leading and trailing edges, and is rotatable about an axis along a movable flap span over a range of angular positions between open and closed. The trailing surface has a substantially U-shaped profile with first and second branches respectively partially around the pressure and suction sides. The transfer slot has inlet and exhaust ports respectively on the pressure and suction sides. In the closed position the suction side contacts the second branch closing the exhaust port, and in the open position the second branch directs a first air flow through the transfer slot tangentially over the suction surface.

Abstract: A nozzle system includes a static structure including a multiple of convergent flap rails and a synchronization ring including an inner ring radially spaced from an outer ring via a multiple of struts. The multiple of convergent flap rails extend at least partially between the inner ring and the outer ring.

Abstract: A blade arrangement of a jet engine or an aircraft propeller including a blade with a root portion and an aerofoil portion, wherein the aerofoil portion includes a suction side and a pressure side. The blade arrangement further includes a retention structure that is configured to radially retain the blade in case of a structural blade failure, wherein the retention structure is secured to the root portion and/or to a structure adjacent to the root portion and extends in the radial direction along the suction side and along the pressure side of the aerofoil portion. The retention structure forms a loop that runs at least around the root portion, along the suction side and along the pressure side of the blade.