Abstract: Mineral particles may provide for wellbore fluids with tailorable properties and capabilities, and methods relating thereto. Mineral particles may be utilized in methods that include introducing a wellbore fluid having a density of about 7 ppg to about 50 ppg into a wellbore penetrating a subterranean formation, the wellbore fluid comprising a base fluid and a plurality of mineral particles, and the wellbore fluid having a first viscosity; contacting at least some of the mineral particles with a linking agent so as to link the at least some of the mineral particles, thereby increasing the first viscosity to a second viscosity.

Abstract: An exchanger for a tank is described herein. The exchanger may be relied upon in a trailer tank, for example, or any other type of tank that stores fluid. The exchanger includes an inlet, a central fluid conduit, one or more exchanger extension arms having fluid apertures that direct fluid into a tank at various locations, and one or more supports that support the central fluid conduit and the exchanger extension arms. The fluid apertures may be positioned relatively evenly across the exchanger extension arms and/or the central conduit to direct fluid up or at various directions into the tank. Thus, fluid pumped into the inlet of the exchanger may flow through the central conduit, into the exchanger extension arms, and out through the fluid apertures at various locations into the tank. As such, heated fluid, for example, may be more evenly and quickly distributed into the tank.

Abstract: An aqueous composition comprising a mineral acid, a fixing agent and water present in an amount sufficient to dissolve the mineral acid and the fixing agent. The fixing agent comprises at least one of an amine and/or an amide containing compound having a dipole moment of at least 3 when in the aqueous composition.

Abstract: The complexity of a fracture network may be enhanced during a hydraulic fracturing operation by monitoring operational parameters of the fracturing job and altering stress conditions in the well in response to the monitoring of the operational parameters. The operational parameters monitored may include the injection rate of the pumped fluid, the density of the pumped fluid or the bottomhole pressure of the well after the fluid is pumped. The method provides an increase to the stimulated reservoir volume (SRV).

Abstract: A method for producing fractures in a formation to release hydrocarbons (such as a hydrocarbon gas or liquid) from the formation is disclosed. The method comprises reducing the in-situ temperature at a location in a formation having a first temperature by contacting the location with a first fluid and contacting the location with a fracturing fluid to produce fractures in the formation while the location is at a second temperature below the first temperature to release hydrocarbons from the formation. The method can include using an endothermic process to reduce the temperature at the location in the formation.

Abstract: A well treatment fluid containing borated galactomannan may be used to isolate a productive zone in a well having multiple productive zones. The fluid is particularly useful in treatment of wells containing a mechanical zonal isolation system in the productive zone of interest. The fluid is pumped into the well in a substantially non-hydrated form. The well treatment fluid is therefore highly effective in preferentially sealing or blocking productive zones in the formation since delayed hydration of the fluid may be controlled for up to several hours. The seal may be degraded and a productive zone subjected to re-fracturing by introducing a viscosity reducing agent into the well.

Abstract: The flow of well treatment fluids may be diverted from a high permeability zone to a low permeability zone within a fracture network within a subterranean formation by use of a mixture comprising a dissolvable diverter and a proppant. At least a portion of the high permeability zone is propped open with the proppant of the mixture and at least a portion of the high permeability zone is blocked with the diverter. A fluid is then pumped into the subterranean formation and into a lower permeability zone of the formation farther from the wellbore. The diverter in the high permeability zones may then be dissolved at in-situ reservoir conditions and hydrocarbons produced from the high permeability propped zones of the fracture network. The mixture has particular applicability in the enhancement of production or hydrocarbons from high permeability zones in a fracture network located near the wellbore.

Abstract: A well pump assembly includes rotary pump and a submersible motor. A shroud surrounds the pump intake and the motor. The shroud has an open upper end in fluid communication with the pump intake. A tubular member of smaller diameter is secured to and extends downward from a lower end of the shroud. The tubular member may have an open lower end for drawing well fluid along a lower flow path up the tubular member to the pump intake. An upper flow path at the upper end of the shroud may have a minimum flow area that is smaller than a minimum flow area of the lower flow path. The tubular member has a smaller outer diameter than an outer diameter of the shroud. The tubular member may have a closed lower end to define a debris collection chamber with a drain valve.

Abstract: The invention provides a control system and method for limiting vibrations in a tool string system, comprising a relatively heavy rotatable device, such as a pump system or a bottom hole assembly, connected to a long rotatable tool string driven by a drive system. The control system comprises feedback of both torque and rotational speed signals to correct the set rotational speed. An objective is to maintain the drive speed over torque ratio equal to the connected tool string impedance. A secondary objective, for lower frequencies, is to approach and maintain a setpoint speed as drive rotation speed. The system may include a rotational speed sensor and a torque sensor, with the latter optionally replaced by a motor torque signal already available from a variable frequency drive (VFD) for an AC motor and the current safeguarding signal for a DC motor.

Abstract: A method (50) and an assembly (10) for milling an obstruction disposed within a wellbore (W) includes a milling module (12) having a motor (22) rotating a milling bit (14), a first electronics cartridge (26) for controlling the motor based upon a motor torque value, a tractor module (16, 18) for engaging with the wellbore and providing a push force against the wellbore to urge the milling assembly in a direction of the milling bit, and a second electronics cartridge (28) for controlling a push force value of tractor module. The method involves rotating the milling bit (54) and engaging the tractor module with the wellbore (56), and adjusting, iteratively, the operation (58) based on a calculated torque value and a calculated push force value to maintain the calculated values at around a target torque value and below a push force limit value (66, 70).

Abstract: The disclosure, in one aspect, provides a method of drilling a wellbore that includes features of drilling the wellbore using a drilling assembly that includes a drill bit that further includes a weight sensor and a torque sensor, determining weight-on-bit using measurements from the weight sensor and torque-on-bit using measurement from the torque sensor during drilling of the wellbore, obtaining measurements for rotational speed of the drill bit and rate of penetration of the drill bit during drilling of the wellbore, determining mechanical specific energy of the bottomhole assembly using the determined weight-on-bit, torque-on-bit and obtained rotational speed of the drill bit and the obtained rate of penetration of the drill bit, and altering a drilling a parameter in response to the determined mechanical specific energy.

Abstract: A hydraulic fracturing system with pump failure detection includes an engine, transmission, hydraulic fracturing pump and a driveshaft coupled between the transmission and the hydraulic fracturing pump to transfer torque from the engine to the hydraulic fracturing pump. A torque sensor is positioned and configured to measure torque acting on the driveshaft, with the torque sensor generating torque measurement data. A controller is programmed to analyze the torque measurement data and identify a pump failure mode based on the torque measurement data.

Abstract: A method and apparatus for ranging from ahead of a drill bit is described. The ranging apparatus includes a ranging probe with at least one sensor that may be deployed ahead of the drill bit. The ranging probe may be conveyed via a cable through the interior of a drill string. In an alternative embodiment, the ranging probe may be attached to a ram that is seated inside of the drill string and that may be extended and retracted. In such an embodiment, the ranging probe may be retrievable by cable. The ranging probe optionally includes collapsible arms that retract when the ranging probe is inside the drill string or drill bit and that extend when the ranging probe is deployed ahead of the drill bit. One or more ranging sensors may be coupled to the collapsible arms. Ranging measurements may be communicated to the surface using telemetry.

Abstract: A downhole tool includes a tool body having an outer surface portion and an inner surface portion and a recess formed in one of the outer surface portion and inner surface portion. At least one removable electronic component access member is detachably mounted to the tool body. The removable electronic component access member provides access to electronic components housed in the recess. A metallic seal is provided on at least one of the tool body and the removable electronic component access member. The metallic seal prevents fluid ingress into the recess through the at least one removable electronic component access member.

Abstract: Systems and methods for identifying formation boundaries without necessarily obtaining an azimuthal borehole image are provided. A downhole tool may be placed in a wellbore in a geological formation that has a formation boundary. First and second measurements may be obtained at a number of depths of the wellbore. The first measurement may have a first effective penetration length into the geological formation and the second measurement may have a second effective penetration length into the geological formation different from the first effective penetration length. Thus, the first measurement may detect the formation boundary at a first depth and the second measurement may detect the formation boundary at a second depth. Using a difference between the first depth and the second depth, an apparent relative angle between the wellbore and the formation boundary or an apparent formation dip, or both, may be obtained.

Abstract: A system and method for determining drilling parameters based on hydraulic pressure associated with a directional drilling system are disclosed. A drilling parameter associated with a directional drilling system may be determined by measuring hydraulic pressure associated with the directional drilling system during drilling of a wellbore, detecting a change in the hydraulic pressure, and determining a drilling parameter based on the detected change in hydraulic pressure.

Abstract: A well tool can include a magnetic sensor having opposite sides, and a magnetic shield that conducts an undesired magnetic field from one side to the other side of the sensor. Another well tool can include a magnetic sensor in a housing, the sensor having opposite longitudinal sides relative to a housing longitudinal axis, and a magnetic shield interposed between the housing and each of the opposite longitudinal sides of the magnetic sensor. Another well tool can include at least two magnetic sensors, one magnetic sensor sensing a magnetic field oriented orthogonal to the housing longitudinal axis, and another magnetic sensor sensing a magnetic field oriented parallel to the longitudinal axis, and a magnetic shield interposed between a housing and each of opposite longitudinal sides of the magnetic sensors.

Abstract: A magnetic system for determining the location of a wellbore component in a first string relative to a wellbore component in a second string. The system includes a circumferentially distributed array of magnets positioned in the first string that is operable to produce a magnetic field in the wellbore proximate the location of the array of magnets. A magnetic field detector is operably associated with the second string and is operable to detect a magnetic signature of the magnetic field. One of the first and second strings is stationary within the wellbore. The other of the first and second strings is moveable in the wellbore such that the magnetic field detector is moveable relative to the magnetic field and such that when the magnetic field detector identifies the magnetic signature, the location of the array of magnets is correlated with the magnetic field detector.

Abstract: A range of apparatus and methods for providing local and long range data telemetry within a wellbore is described. These apparatus and methods may be combined in a wide variety of ways. In some embodiments data is transmitted across a gap in a drill string using signals of a higher frequency for which an electrical impedance of the gap or of a filter connected across the gap is low. Low-frequency EM telemetry signals may be applied across the gap. The gap and any filter connected across the gap present a high impedance to the low-frequency EM telemetry signals. The described technology may be applied for transferring sensor readings between downhole electrical packages. In some embodiments sensors are electrically connected across electrically insulating gaps in the drill string.

Abstract: A system for automated collection of cutting samples produced during the drilling of a well includes an automated valve system for periodically collecting samples including fluid and cuttings from a flow line from a drilling rig and a packaging system for packaging each sample collected from the flow line. The packaging system deposits each sample received from the valve system at a corresponding point along a moving elongated strip of base material, covers the elongated strip of base material and samples deposited on the base material with a strip of cover material, and advances the covered elongated strip of base material and covered samples onto a reel.

Abstract: A mining machine including a chassis, an actuator, a cutter drum supported by the chassis, the cutter drum driven by the actuator, a cutter bit coupled to the cutter drum, and a controller. The controller includes a processor and memory and is configured to measure a characteristic of the actuator, determine the cutter bit is worn based on the measured characteristic of the actuator, and output a signal when the cutter bit is determined to be worn.

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

Abstract: A rotor disc (1) for a turbomachine, including a radial flange (2) that includes a plurality of fastening holes (3), and a plurality of scallops (4) forming notches in the flange (2), and being separated by inter-scallop flange portions (7). The flange alternatively has, in its circumferential direction: a fastening hole (3) and an inter-scallop flange portion (7) arranged in the radial extension of the fastening hole (3), and a scallop (4), in such a way that one or more of the scallops (47, 48, 49; 42, 45-47, 48-411, 414) has a volume greater than the volume of each of the other scallops (41-46, 410-414; 41, 43, 44, 412, 413), and one or more of the inter-scallop flange portions (73) has a volume less than the volume of each of the other inter-scallop flange portions (71, 72, 74), in order to balance said disc (1). A turbomachine including that rotor disc and a method for balancing a turbomachine rotor disc are also disclosed.

Abstract: An assembly for a gas turbine that engine includes a fan section. A turbine section is configured to drive the fan section. The turbine section includes a rotor hub with a rotor lug. A heat shield engages the rotor lug. The heat shield and the rotor lug define a cooling passage.

Abstract: A steam turbine with a resonance chamber in the outer annulus opposite a rotating blade row. The resonance chamber provides passive resonance to place the excitation at a frequency away from the natural frequency of the blades.

Abstract: A propeller blade includes an inner spar structure surrounding an inner spar foam core. Also included is a leading edge foam structure disposed proximate a leading edge of the inner spar structure. Further included is a trailing edge foam structure disposed proximate a trailing edge of the inner spar structure. Yet further included is an outer spar structure surrounding the inner spar structure, the leading edge foam structure and the trailing edge foam structure. Also included is a blade shell, a leading edge foam core located between the outer spar structure and the blade shell, and a trailing edge foam core located between the outer spar structure and the blade shell.

Abstract: A wind turbine blade (1) is formed of a fiber-reinforced composite material comprising a polymer matrix. The blade (1) further comprises a first region (11), a second region (12) and a transition region (13) between the first and the second region (11, 12). The first region (11) is reinforced predominantly with a first reinforcement fiber material (21). The second region (12) is reinforced predominantly with a second reinforcement fiber material (22). The first and the second reinforcement fiber material differ from each other and has differing E-modulus. The transition region (13) additionally comprises a third type of reinforcement fiber material (23) differing from both the first and the second reinforcement fiber material (21; 22) and having an E-modulus between that of the first reinforcement fiber material (21) and that of the second reinforcement fiber material (22).

Abstract: A method of disassembling reinforcement from a part, the method including: fastening at least one metal stud on one side wall of the reinforcement and at least one other metal stud on the other side wall of the reinforcement, the studs extending substantially perpendicularly to the side walls on which they are fastened; moving the studs apart from each other to space apart the side walls of reinforcement and disengage snap-fastener mechanisms thereof from complementary mechanisms of the part; and removing the reinforcement from the part.

Abstract: A moving blade of a low pressure turbine includes a foot and a vane having an upper surface and a lower surface, the foot having a stilt linking the vane to the foot, wherein the stilt is formed such that the transverse section of the stilt has: a first straight portion, a second curved portion and a third straight portion, the curved portion having an outer face matching the profile of the upper surface of the vane and an inner face matching the profile of the lower surface of the vane.

Abstract: A component for a gas turbine engine includes an airfoil that has a first end. A first platform is located at the first end of the airfoil. A compound fillet includes a first fillet portion tangent to the first platform and an airfoil offset. A second fillet portion is tangent to a surface of the airfoil and the first fillet portion.

Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs.

Abstract: The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.

Abstract: An exemplary gas turbine engine assembly includes a damping device having a first side and a second side facing away from the first side. The first side is configured to hold a seal when the second side engages an extension from a gas turbine engine component. The first side is further configured to engage the extension when the second side holds the seal.

Abstract: A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

Abstract: A gas turbine combustion chamber is provided, including a flow sleeve structure with an improved anti-vibration performance. A gas turbine combustion chamber of the present invention includes a liner, a transition piece, and a flow sleeve including a plurality of segments and integrated by welding a tie piece along joint portions of the segments. The tie piece includes a first member and a second member, the first member continuously extending along a longitudinal direction of the joint portions of the segments and being arranged to cover the joint portions, and the second member being formed at an end portion of the first member, having a width wider than the first member, and including a recess.

Abstract: An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

Abstract: A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

Abstract: Aspects of the present invention relate to systems and methods of a vane design utilizing welding techniques. The present invention concerns a method for preventing cracking within a vane assembly utilizing full penetration welding. Additional embodiments concern a vane design that, when assembled with another vane, comprises an axial slot that prevents cracking within a vane assembly.

Abstract: A distributor device for distributing cooling air within a gas turbine engine, the device including a base mountable adjacent an inlet for air to be distributed; and a deflector supported by the base and in fluid communication with the air inlet, the deflector being configured to direct air from the air inlet in a plurality of directions within the engine; wherein the deflector includes one or more deflecting surfaces curvilinearly configured to direct the air differentially in a plurality of desired directions within the engine. In embodiments the deflecting surface(s) is/are curved and are so configured such that air from the air inlet is directable either: (i) in directions of travel in each of a plurality of desired different, non-parallel directions within the engine; or (ii) in each of a plurality of desired different directions within the engine with different flow rates.

Abstract: A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

Abstract: Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system.

Abstract: Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.

Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.

Abstract: System, method and apparatus providing power generation and demand management using a thermal hydraulic generator. Also a more efficient (full time cycle) and stable thermal hydraulic generators and heat exchangers are disclosed.

Abstract: A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively.

Abstract: An example method of assembling a particle damped gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, holding damping media within a cavity of a gas turbine engine component using magnetic force.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. At least one spoke includes an inlet passage with at least one branch extending in an axial direction in fluid communication with the fluid passage in the inner frame case. A fitting fluidly connects the at least one branch to the fluid passage in the inner frame case. The fitting also includes a transfer tube connecting the cooling airflow passage to a cup boss. The transfer tube is fixed relative to the cylindrical portion and moveable relative to the cup boss. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.

Abstract: A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45.