Abstract: A method for controlling the liquid load size of a plunger lift well during the shut in time of the well to facilitate a controlled plunger rise. Intra-cycle control allows dynamic adjustments within a cycle to keep the plunger running and not stalling out or rising too fast. The method includes the steps of shutting in the well to build up pressure within the well, adjusting a size of a liquid slug within the tubing while the well is shut in, opening a valve to relieve pressure within the well and raise the plunger within the tubing, pushing the liquid slug out of the well with the plunger, and closing the valve wherein the plunger falls within the tubing. The intra-cycle adjustments include reducing the size of the liquid slug for preventing fluid loading and increasing the size of the liquid slug for controlling a rise rate of the plunger.

Abstract: Embodiments provide a system, apparatus and method for artificial lift including a hydraulic downhole rodless pump actuator.

Abstract: Optimized enhanced oil recovery can include tuning of injection rates during a recovery operation. The injection rate of injection fluid pumped into a formation can be controlled to alternate between monotonically increasing and monotonically decreasing during the enhanced recovery operation. Injection rates can be monotonically increased to a maximum level (e.g., as defined by physical constraints of the system) and then monotonically decreased to a lower level, allowing the injection rates to be monotonically increased again. While injection rates are monotonically increasing, viscous fingering between the injection fluid and hydrocarbons can be minimized while the hydrocarbons in the formation are displaced. While injection rates are monotonically decreasing, creation of new viscous fingers can be minimized while the injection rates are decreased to levels suitable for the monotonic increasing phase of a subsequent monotonic cycle.

Abstract: The disclosed embodiments include a computer implemented method, apparatus, and computer program product that includes executable instructions that when executed performs operations for determining flow control device (FCD) properties for an injection well that yields uniform flooding along the production well.

Abstract: Producing hydrocarbons by steam assisted gravity drainage, more particularly, utilizing conventional horizontal wellpair configuration of SAGD in conjunction of infill production well, to coinject oil-based solvents with steam initially and then switch to NCG-steam coinjection after establishing thermal communication between the thermal chamber and infill well.

Abstract: A hydraulic fracturing system for fracturing a subterranean formation includes a power generation system, a transmission section, and an equipment load section. The power generation system includes a turbine generator that generates electricity that is used to power equipment in the equipment load section. The equipment in the equipment load section conditions and pressurizes fluid that is injected into a wellbore for fracturing the formation. The power generation and equipment load sections are distal from one another are separated by a long distance. The transmission section connects the power generation and equipment load sections, and thus spans the long distance between these sections.

Abstract: A system for controlling drilling unit apparatus includes a plurality of drilling unit apparatus each operated by a corresponding controller. Any one or more of the controllers is in signal communication with either or both of (i) at least one sensor that generates a signal related to an operating condition of the drilling unit apparatus and (ii) at least one other of the controllers to accept as input therefrom a signal related to an operating state of the corresponding drilling unit apparatus. A plurality of time reference signal receivers is each in signal communication with a corresponding controller. An absolute time reference signal transmitter is in signal communication with each time reference signal receiver such that any one or more of the controllers operates its respective drilling apparatus in response to either or both of (i) the sensor signal and (ii) the signal from the at least one other controller.

Abstract: A well monitoring system may provide a plurality of integrated chips dispersed in cement surrounding a well casing. Each of the integrated chips may provide energy harvesting circuitry, EM transceiver, modulator, additional sensor(s), processor or microprocessor, memory, power source, or the like. Upon analyzing data gather from the sensor(s), emitted and detected EM waves, the system may provide information about the cement thickness at different parts of the well, cement setting/curing, local electrical permittivity, local magnetic permeability, temperature, pressure, pH, local NMR spectrum, local ESR spectrum, local florescence response, local porosity, local permeability, etc. Further, the integrated chips may be utilized to transmit/receive the abovementioned data, other data (e.g. command data, power signal, etc.), or the like to/from the main transceiver.

Abstract: Reelable sensors arrays are independently fabricated separate from a downhole tubular. The sensor arrays are then reeled together onto a spool. At the well site, the sensor array is unreeled from the spool and attached to the tubular as it is deployed downhole, resulting in a fast and efficient method of sensor deployment.

Abstract: A method that includes deploying an acoustic caliper tool in a borehole, the tool having several axially-spaced acoustic transceivers; obtaining acoustic signal reflection measurements for the transceivers; estimating a distance-to-boundary value for the transceivers based on reflection measurements; calculating a tool inclination angle based on the distance-to-boundary values; and deriving a correction value based on the angle. A system that includes an acoustic caliper tool having several axially-spaced acoustic transceivers to obtain reflection measurements; at least one processor; and at least one memory in communication with the processor, the memory storing instructions that cause the processor to: receive the acoustic signal reflection measurements; estimate a distance-to-boundary value for the transceivers based on the reflection measurements; calculate a tool inclination angle based on the distance-to-boundary values; and derive a correction value based on the angle.

Abstract: Methods and systems for depth and radial orientation detection are provided. Methods for determining the depth or radial orientation of one or more downhole components include the steps of providing a target mass and a using a detection device for detecting the depth and/or orientation of the target mass. In some cases, the target mass is initially nonradioactive and then, after installing the target mass downhole, it may be irradiated to form a relatively short-lived radioactive target mass, which may then be detected with a radiation detector. In this way, the target mass acts as a depth or radial orientation marker. Where the target mass is situated downhole in a known radial relationship to another downhole component, the radial orientation of the other downhole component may be deduced once the radial orientation of the target mass is determined. Advantages include higher accuracies and reduced health, safety, and environmental risks.

Abstract: Provided are systems and methods for in-situ zonal assessment of multiphase fluid flow in one or more production zones of a production well, including for at least one production zone sensing one or more fluid flow parameters via at least one sensor disposed in a production zone; at least one sensor communications node being in electrical communication with an associated sensor, the at least one sensor communications node positioned along a tubular body in the production zone proximate an associated at least one sensor, and receiving signals from the associated at least one sensor; sending the acoustic signals from the at least one sensor communications node to a receiver at a surface via a series of intermediate communications nodes, node-to-node, the signals being indicative of one or more fluid flow parameters, the series of intermediate communications nodes being spaced along the tubular and configured to transmit acoustic waves; assessing one or more fluid flow parameters for the one or more production z

Abstract: A system for active noise blocking of top drive acoustical waves includes a first accelerometer for detecting a first acoustical wave generated by the top drive of a drilling rig. A second accelerometer detects a second acoustical wave after the first acoustical wave has interacted with an anti-wave. An active noise blocking generator generates the anti-wave responsive to the detected first acoustical wave and the detected second acoustical wave and applies the anti-wave to the first acoustical wave. The anti-wave is generated to drive the second acoustical wave to zero responsive to application of the anti-wave to the first acoustical wave.

Abstract: A method includes identifying one or more stress regime types along at least a portion of a borehole, where the stress regime types are selected from a normal stress regime, a thrust stress regime and a strike-slip stress regime, and selecting reservoir access locations along the borehole based on the type of stress regime identified along the borehole.

Abstract: A device for cutting a block of stone that includes a support bar including a monolithic metallic plate. The device also includes a wear bar that is secured to the monolithic metallic plate and has a longitudinal slot, and a cutting belt positioned in the longitudinal slot of the wear bar and including a cutting surface to cut the stone. A method of cutting the stone is also disclosed.

Abstract: A turbine of an organic Ranking cycle (ORC) is described. The turbine includes a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor blades. The rotor blades are sustained by corresponding supporting disks. A main supporting disk is directly coupled to the shaft in an outer position with respect to the bearings, and the remaining supporting disks are constrained to the main supporting disk, and one to the other in succession, but not directly to the shaft. Some of the remaining supporting disks are constrained to the main supporting disk and cantileverly extend from the same side of the bearings that support the shaft, so that the center of gravity of the rotor part of the turbine is shifted more towards the bearings.

Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.

Abstract: A propulsor for a gas turbine engine may comprise a case including a duct disposed along an axis to define a flow path, a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path, and a row of guide vanes situated in the flow path. A first guide vane may comprise a radially inner length (LI), a radially outer length (LO), and a midspan length (LM). The first guide vane may have a first dimensional relationship defined as LO/LM. The first guide vane may have a second dimensional relationship defined as LI/LM. The first dimensional relationship and/or the second dimensional relationship may be greater than 1.05.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane, a second turbomachine blade or vane adjacent to it, and at least one tuning element guide housing with at least one cavity, in which at least one tuning element is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess, in particular in a frame, of the first turbomachine blade or vane, where the second turbomachine blade or vane has at least one first rib for securing the tuning element guide housing arranged in the recess.

Abstract: A gas turbine engine component includes a wall portion that includes a first side and a second opposite side. A plurality of passages extends between the first side of the wall portion and the second side of the wall portion and includes a plurality of inlets located on the first side of the wall portion. A plurality of outlets are located on a second side of the wall portion. The plurality of outlets include a first plurality of outlets located on a first side of the plurality of inlets and a second plurality of outlets located on a second side of the plurality of inlets.

Abstract: An airfoil may include an airfoil body that defines a central chamber, a skin chamber, and an impingement hole extending between the central chamber and the skin chamber. The central chamber may be in fluidic communication with the skin chamber via the impingement hole. In various embodiments, a first cross-sectional area of the impingement hole is greater than about 25% of a second cross-sectional area of the skin chamber. In various embodiments, the impingement hole is positioned and configured to deliver cooling circuit air to a predicted position of a hotspot on a surface of the airfoil. In various embodiments, the airfoil body further defines at least one structural hole formed from at least one structural core tie, wherein a first cross-sectional area of the impingement hole is at least twice a second cross-sectional area of the at least one structural hole.

Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion.

Abstract: A turbine component including a shrouded airfoil with a flow conditioner configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner is positioned on a shroud base radially adjacent to the tip of the airfoil and includes a ramped radially outer surface positioned further radially inward than a radially outer surface of the shroud base. The ramped radially outer surface extends from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge. Multiple coolant ejection holes are positioned on the ramped radially outer surface. The coolant ejection holes are connected fluidically to an interior of the airfoil.

Abstract: A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).

Abstract: Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

Abstract: The method of protecting a component of a turbomachine from liquid droplets erosion provides covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine with a protective layer. The protective layer consists of a plurality of adjacent sub-layers of different materials having high hardness in the range of 1000-3000 HV and low fracture toughness below 20 MPam1/2. The materials are typically nitrides or carbides of titanium or aluminum or chromium or tungsten. In an embodiment, the covering is carried out by a PVD technique, in particular by Cathodic Arc PVD, or a CVD technique. The method may be applied to any component of turbomachines, but it may be particularly beneficial for parts of centrifugal compressors.

Abstract: A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.

Abstract: An asymmetric vane assembly includes a high count vane section including a first plurality of vanes oriented in a first position. The asymmetric vane assembly also includes a low count vane section including a second plurality of vanes oriented in a second position, a total number of vanes in the first plurality of vanes being greater than a total number of vanes in the second plurality of vanes, and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.

Abstract: A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.

Abstract: A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner.

Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.

Abstract: A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed.

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

Abstract: A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring.

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 gas turbine engine includes a compressor having a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine has a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. A low speed accessory gearbox is interfaced with the first shaft via a mechanical interface. The low speed accessory gearbox includes a mechanical brake.

Abstract: In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle ?ADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle ? at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle ?ADP and the off-design point fan tip leading edge relative flow angle ? is in a specified range.

Abstract: A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.

Abstract: A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

Abstract: An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.

Abstract: An engine arrangement includes a first engine unit, a second engine unit and at least one member for fastening the second engine unit to the first engine unit. The first unit and the second unit include fluid ports for achieving a fluid flow between the first and second unit. The engine arrangement further includes a valve for opening and closing at least one of the fluid ports and the fastening member is moveably arranged relative to the first unit and second unit and is arranged to act on the valve.

Abstract: A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool.

Abstract: A turbine engine casing, and in particular an axial turbine engine compressor casing, includes an annular wall and a fastening flange associated with the wall. The fastening flange includes a fastening surface applied against a corresponding mounting surface of the turbine engine, for example, a surface on an intermediate fan casing or a mounting surface of a flow separator. The fastening flange includes at least one electrical connector with one end lying flush with the fastening surface of said fastening flange.

Abstract: An anti-rotation shroud dampening pin is disclosed including a shaft, an anti-rotation dampening tip at a first end of the shaft, and a cap at a second end of the shaft. The anti-rotation dampening tip includes a pin non-circular cross-section. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the anti-rotation shroud dampening pin, and a biasing apparatus. The inner shroud includes an anti-rotation depression having a depression non-circular cross-section. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud. The anti-rotation shroud dampening pin is disposed within the channel and in contact with the inner shroud, and extends through the aperture into the anti-rotation depression. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the anti-rotation dampening tip. The pin non-circular cross-section mates non-rotatably into the depression non-circular cross-section.

Abstract: A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.

Abstract: A control device includes a mode-recognizing unit that recognizes whether a start mode of a steam turbine is a cold mode in which a temperature of a steam contact portion of the steam turbine is lower than a predetermined temperature or a different start mode in which the temperature of the steam contact portion is equal to or higher than the predetermined temperature, a first opening generator that generates a first degree of opening greater than a second degree of opening in the different start mode as a degree of opening of an intake air regulator of a compressor in a period after generation of steam from an exhaust heat recovery boiler is started and before supplying of the steam to the steam turbine is started, and a command output unit that outputs a command corresponding to the first degree of opening to the intake air regulator.

Abstract: A thermodynamic cycle such as an organic Rankine cycle system, utilizing a lubricant and a working fluid, for a machine in which pressurized gaseous working fluid is expanded to a lower pressure level and the energy from the fluid expansion is transformed into mechanical rotation energy; the lubricant includes a polyalkylene glycol based lubricant composition and the working fluid includes a mixture of alcohol and water.

Abstract: The present invention relates to a supercritical CO2 power generation system of a series recuperative type. According to an embodiment of the present invention, an inlet temperature of a turbine can be increased to increase a work of the turbine, thereby realizing a cycle design having improved turbine efficiency. Further, the number and diameter of pipes connected to a heat exchanger using an external heat source can be reduced to reduce the plumbing related costs, thereby improving economical efficiency.

Abstract: An exhaust valve rocker arm assembly operable in a combustion engine mode and an engine braking mode can include a rocker shaft and a rocker arm. The rocker shaft can define a pressurized oil supply conduit. The rocker arm can receive the rocker shaft and is configured to rotate around the rocker shaft. The rocker arm can have an oil supply passage defined therein. A valve bridge can engage a first exhaust valve and a second exhaust valve. An accumulator assembly can be disposed in the rocker arm and includes an accumulator piston that translates within the accumulator piston housing between closed and open positions. A predetermined amount of oil is stored in the accumulator assembly.