Abstract: The present invention provides a drilling auxiliary system, which establishes one or more links among multiple wells or among different branches of the same well. When the present invention is applied to the EM data transmission, it can significantly reduce unwanted electric energy consumption in the formation, thus effectively improve data transmission efficiency. When the present invention is applied to the casing detection, it can achieve a large detection range and greatly simplify the complexity of the operation, thereby saving costs.

Abstract: A method of amplifying a data-encoded acoustic signal in an oil or gas well system comprising: performing at least a first transmission of the data-encoded acoustic signal from a transmitter towards a receiver, wherein at least some of the data-encoded acoustic signal is reflected from a well system object; providing an impedance mismatch point; and causing or allowing amplification of the data-encoded acoustic signal, wherein the amplification is due to the well system object, the impedance mismatch point, and the transmitter.

Abstract: A system and method of transmitting measurement-while-drilling (MWD) data while drilling a wellbore in a subterranean formation are provided. The system utilizes a transmission sub located uphole of the drill bit which transmits an electromagnetic signal through the surrounding drilling fluid to a receiver assembly located farther uphole at a position suitable for relaying the signal to the surface.

Abstract: In an example diagnostic fracture injection test (DFIT), or a “minifrac,” a fracturing fluid is pumped at a relatively constant rate and high pressure to achieve a fracture pressure of a subterranean formation. Sometime after achieving formation fracture pressure, the pump is shut off and the well is shut in, such that the pressure within the sealed portion of the well equilibrates with the pressure of the subterranean formation. As the pressure declines, the pressure of the injection fluid is monitored. This collected pressure data is then used to determine information regarding the permeability of the subterranean formation. In some implementations, a model for before closure analysis (BCA) can be used to estimate the permeability of a formation based on before closure pressure data (i.e., data collected before the fracture closure pressure is reached) based on a solution to the rigorous flow equation of fracturing fluid, which is leaking off into the formation during fracture closure.

Abstract: A method for determining a volume of a constituent(s) in a geological formation may include generating an equation of state based upon log measurements for the geological formation, with the equation of state providing a correlation between the log measurements, determining a quality factor for the equation of state, and for each of a plurality of different constituents expected to be in the formation, determining a constituent compliance factor for each of the constituents. The method may further include determining an uncertainty for each constituent compliance factor, determining a likelihood that each constituent is present in the formation based upon the quality factor, the constituent compliance factor for the constituent, and the uncertainty for the constituent compliance factor, generating a volumetric model based upon the log measurements and the determined likelihoods of the constituents in the formation, and determining the volume of the constituent(s) based upon the volumetric model.

Abstract: A method for estimation of water properties and hydrocarbon properties in a subsurface formation includes acquiring a plurality of well log measurements from the subsurface formation. The water properties and the hydrocarbon properties are parameterized with respect to a selected set of well log measurements. A simultaneous or sequential inversion is performed to estimate the water properties and the hydrocarbon properties.

Abstract: A method of tracing flow of hydrocarbon from a subterranean reservoir including forming a dispersion, injecting a hydraulic fracturing fluid containing the dispersion down a well penetrating a hydrocarbon reservoir, thereafter collecting a sample of hydrocarbon fluid flowing from the reservoir, and analysing the sample to determine whether the tracer compound is present in the sample. The dispersion includes a discontinuous condensed phase having a hydrocarbon-soluble tracer compound and a continuous phase which includes an aqueous liquid.

Abstract: The invention relates to a chisel (10) having a chisel head (11) and a chisel shaft (17), wherein near its end facing away from the chisel head the chisel shaft has a threaded portion having a thread (19), wherein the chisel head holds a chisel tip (20) made of a hard material, and wherein near the side facing the chisel shaft the chisel head is provided with a supporting surface (15). Especially when superhard hard materials are used for the chisel tip, a load-optimized chisel design is obtained by a domed supporting surface (15).

Abstract: A boring machine comprises a forward section, a rear section, a parallel link mechanism, stroke sensors, pressure sensors, and a controller. The parallel link mechanism includes eight thrust jacks that change the position and attitude of the forward section with respect to the rear section. The controller computes a target allocation force to be allocated to eight thrust jacks on the basis of the sensing result from the stroke sensors and the pressure sensors, and controls the thrust jacks to perform stroke control on six of the thrust jacks and perform force control on two of the thrust jacks.

Abstract: A boring machine comprises a forward section, a rear section, an articulation point, a parallel link mechanism, an input component, an articulation point position computer, and a jack controller. The parallel link mechanism includes a plurality of thrust jacks that change the position of the forward section with respect to the rear section. The articulation point position computer computes the position of the articulation point on the basis of the control inputs received by the input component, and the positions of the center line and center point of the rear section and the center point of the forward section. The jack controller controls the stroke amounts of the thrust jacks to produce movement corresponding to a curve generated from the positions of the center point of the rear section, the articulation point, and the center point of the forward section.

Abstract: A pin retaining assembly for an advancing ram includes a retention plate and a retainer. The retention plate includes two oppositely facing surfaces and a channel with a notch between the two surfaces. The retainer includes a main body, a pin receiving slot, and at least two flanges. The main body is configured to slide into the notch of the channel and extend through a surface of the retention plate. The pin receiving slot has an open mouth through an end of the main body. A first flange extends from one end of the main body along a surface of retention plate and a second flange extends from another end of the main body along another surface of retention plate. The flanges retain the main body of the retainer in the first notch from moving in a direction defined by a longitudinal axis of the pin receiving slot.

Abstract: An axial piston machine is shown comprising a cylinder drum rotatable around an axis of rotation and having at least a cylinder, a piston arranged in said cylinder, a swash plate arranged in front of said cylinder drum, said piston being provided with a slipper (11) resting against said swash plate and having a pressure area (17) on a side facing said swash plate, wherein a cylinder axis of said cylinder is arranged on a circle line (27) around said axis of rotation (16). Such a machine should be made compact. To this end said pressure area (17) deviates from a circular form.

Abstract: A radial cam engine with an optimized cam configuration can provide improve performance over crankshaft internal combustion engines. The cam configuration can include a flat-top or flat bottom piston motion, multiple lobe cam configurations, matching piston force with torque/force ratio in combustion phase, asymmetry piston motions for improved power transfer during combustion phase, and/or offset piston and cam configurations. The radial cam engine can be used in vehicles, such as hybrid vehicles.

Abstract: Aspects of the disclosure are directed to a servicing of an airfoil of an aircraft engine. A first portion of a first bondcoat layer may be removed from the airfoil while leaving a second portion of the first bondcoat layer intact on the airfoil. A second bondcoat layer may be applied to the airfoil using a coating technique subsequent to the removal of the first portion of the first bondcoat layer.

Abstract: A method for repairing a blade wherein the blade comprises a metallic substrate shaped to define an airfoil having a tip. A coating is on the tip. The method comprises: machining to at least partially remove the coating; plating a nickel-based base layer; and plating an abrasive layer comprising a nickel-based matrix and an abrasive.

Abstract: A rotor includes a rotor hub that is rotatable about an axis. The rotor hub includes a bore portion and a rim. An arm extends axially and radially inwardly from the rim. The arm has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side.

Abstract: A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end.

Abstract: A rotor blade comprises a blade platform and an airfoil. The airfoil comprises a blade tip, a leading edge, and a trailing edge with a stiffening compound lean contour. The blade tip is radially opposite the blade platform, and defines a blade span between the blade itself and the blade platform. The leading and trailing edges extend from the blade platform to the blade tip to define blade chords between the leading edge and the trailing edge. The compound lean contour comprises a positive lean section located at the lean tip, and extending along a lean axis to a lean end. The negative lean section is located radially inward of the positive lean section, and extends along the lean axis to the lean end.

Abstract: A turbomachine includes an endwall with a plurality of circumferentially spaced apart, radially extending blades extending from the endwall. A first one of the blades defines a pressure surface of a flow channel, a second one of the blades defines a suction surface of the flow channel, and the endwall defines an inner surface of the flow channel. The endwall includes a radially raised portion that is raised proximate the suction surface, and a radially depressed portion downstream of the raised portion.

Abstract: A. structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage. A plurality of protrusions are formed within a wall surface of the turn passage. A plurality of protrusions are configured to extend transversely relative to the curved surface. A gas turbine engine component is also disclosed.

Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.

Abstract: A turbomachine component includes a body defining a cooling inlet and a cooling outlet in fluid communication with each other through a cooling channel that defines a longitudinal axis, and at least one pedestal disposed within the cooling channel. The pedestal is angled within the cooling channel relative to the longitudinal axis. The turbomachine component can be a vane, a blade, a blade outer air seal, or a combustor panel.

Abstract: A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.

Abstract: The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.

Abstract: An airfoil component includes an insert that has angled faces joined at an edge that provides an airfoil trailing edge. An outer CMC fiber layer overlaps the angled faces to provide a trailing edge portion of an airfoil.

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component comprising a body and an outer region. The body having a silicon containing ceramic composite. The outer region on an outer surface of the body.

Abstract: A technique for mounting a turbine retention device is provided. The technique comprises forming openings in a diffuser, aligning a mounting bracket with the openings, and installing fasteners through the openings and the mounting bracket. A turbine retention device mounted to a diffuser may is also provided. The turbine retention device may comprise a bullet, wings coupled to the bullet, mounting brackets coupled to the wings, and fasteners disposed through the mounting brackets and openings formed in the diffuser.

Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

Abstract: The invention relates to a turbine diffuser for recovering pressure from a fluid exhausted from a last stage blade, the diffuser. In at least in a region between 10% of the longitudinal length and of the diffuser and a downstream end of the diffuser, the inner guide forms an inflectionless curve and further has a peak radial height at a point between 40%-60% of the longitudinal length.

Abstract: A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.

Abstract: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.

Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.

Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.

Abstract: A containment structure for a gas turbine engine includes a stator shroud with a wall. The stator shroud wall extends axially between a shroud inlet aperture and the shroud outlet aperture. The wall includes a stainless steel alloy material having less than 44% nickel by mass to provide containment protection for an impeller rotateably disposed within an interior of the stator shroud.

Abstract: A rotor disk assembly comprises a circular body configured to rotate about an axis, a contoured slot formed partially through the circular body in an axial direction, and a protrusion extending radially from the circular body adjacent the contoured slot. A turbine or compressor assembly is also provided. The turbine or compressor assembly may include a first disk configured to rotate about an axis, a first contoured slot formed partially through the first disk, a first protrusion adjacent to the first contoured slot and extending radially outward from the first disk, and a first blade disposed in the first contoured slot and configured to engage the first protrusion.

Abstract: A recirculation seal for use within a gas turbine engine. The recirculation seal includes a first seal base, including a first seal base axis. The recirculation seal further includes a second seal base, including a second seal base axis The recirculation seal further includes a resilient bulb member coupled to the first seal base. The resilient bulb member includes an exterior bulb wall and an interior bulb wall, wherein the interior bulb wall defines an interior space.

Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.

Abstract: A gas turbine component for a gas turbine is provided. The gas turbine component has a shell portion having an abradable portion (2) to allow rotor blade ends (1) of a rotor blade array of the gas turbine to rub into the same. The abradable portion adjoins a neighboring portion (3) of the shell portion axially at both sides and is additively manufactured together therewith.

Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) mounted radially outwardly of a blade. The engine further includes a BOAS support. A radial dimension of the BOAS support is selectively changeable in response to a flow of fluid through the BOAS support to adjust a radial position of the BOAS relative to the blade.

Abstract: The present disclosure relates generally to a variable area turbine vane row assembly. In an embodiment, the variable area turbine vane row assembly includes rotatable vanes that are circumferentially biased and/or axially biased with respect to adjacent fixed vanes. In another embodiment, the variable area turbine vane row assembly includes multiple rotatable vanes positioned between adjacent fixed vanes, which may optionally be circumferentially biased and/or axially biased with respect to each other as well as to the adjacent fixed vanes.

Abstract: An assembly can include an exhaust gas turbine housing that includes an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first adjustable divider vane disposed adjacent to the inner wall end; a second adjustable divider vane disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels to the turbine wheel space.

Abstract: A variable geometry turbine turbocharger (1) includes a gear driven adjustment ring actuator mechanism (300) supported within a housing (16) via a resilient mount (70) disposed between the mechanism (300) and housing (16). The gear driven adjustment ring actuator mechanism (300) rotates an adjustment ring (350), which in turn adjusts the position of the vanes (30) of the variable geometry turbine (2). The resilient mount (70) accommodates the heat-related expansion and contraction of the gear driven adjustment ring actuator mechanism (300).

Abstract: A rotor system lock for a gas turbine engine is described which blocks movement of rotating wheel assemblies relative to static vane assemblies in a gas turbine engine in order to block unintended rotation (or windmilling) of the gas turbine engine when it is exposed to high winds while at rest or to ram air during pre-launch flight and thereby avoid damage to components of the engine.

Abstract: A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses.

Abstract: The invention relates to a method (1000) for monitoring a degree of coking at the dynamic seals of a turbine engine comprising: a gas generator, comprising a rotary shaft and an injection wheel mounted on said shaft, an injection manifold, dynamic seals for ensuring a seal between the injection wheel and the injection manifold, and a starter, the method comprising the steps: measuring (1500), during a phase for initiating rotation of the shaft of the gas generator by the starter, a current flowing through the starter and a voltage on the terminals of the starter, determining (1600), from the measured current and voltage, a degree of coking at the dynamic seals. The invention also relates to a turbine engine comprising a system for monitoring a degree of coking.

Abstract: A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches.

Abstract: A turbo-machine is provided having at least one turbo-machine stage, wherein overload protection of the rotating shaft is provided by the method and, to protect the rotating shaft against overload, a measurement of a torsional stress of the rotating shaft is carried out during operation of the rotating shaft. The torsional stress is measured via a measurement of the torque of the rotating shaft. The torque is preferably measured magneto-elastically. By using the measured torque of the rotating shaft, the development of the torque is forecast. On the basis of the forecast produced, the turbo-machine stage or operating parameters of the turbo-machine is/are regulated. Further to a turbo-machine is provided comprising at least one turbo-machine stage which has at least one rotating shaft, wherein the turbo-machine has a device for carrying out the method.

Abstract: Turbines and associated equipment are normally cleaned via water or chemical pressure washing via a mist, spray systems. However, these systems fail to reach deep across the gas path to remove fouling materials. Various embodiments herein pertain to apparatus and methods that utilize the water and existing chemicals to generate a foam. The foam can be introduced at that gas-path entrance of the equipment, where it contacts the stages and internal surfaces, to contact, scrub, carry, and remove fouling away from equipment to restore performance.

Abstract: An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.