Abstract: Embodiments of the present disclosure include a system for positioning a sensor within a flow path of a wellbore annulus including a work string extending into the wellbore annulus from a surface location. The system includes a moveable arm on the work string, the arm transitioning between a first radial location and a second radial location. The system further includes a bracket coupled to the arm, the bracket being pivotable about a pivot axis, wherein the bracket supports the sensor and transitions the sensor from a stored position to a deployed position.

Abstract: A method includes emitting, with one or more sensors of a downhole tool disposed in a borehole, an excitation signal. The method also includes detecting, with the one or more sensors, a returned signal resulting from an interaction of the excitation signal with the borehole. The method further includes estimating a noise of the returned signal. The method also includes quantifying a probability that the estimated noise is not a white noise of the borehole. The method further includes identifying drill cuttings in a predetermined location of the borehole based on said quantification.

Abstract: A tool for detecting leaks in downhole pipe comprises wave generator devices (30, 40) for coupling ultrasound waves into the surrounding fluid. The waves are scattered, e.g. reflected, at inhomogeneities (60) in the fluid, for example particles, scatterers and/or water in oil, thereby generating reflections (70) which are measured with a receiver device (25) and evaluated for determining the positions of the inhomogeneities in the fluid in order to detect e.g. crossflows (15) generated by leakage (65).

Abstract: A method of determining a property within a subterranean formation comprises introducing silica nanoparticles into a well; obtaining a sample of a fluid produced from the well; and analyzing the sample for presence of the silica nanoparticles, wherein the silica nanoparticles comprise a core, a donor chromophore, an acceptor chromophore, and an outer silica shell; the donor chromophore and the acceptor chromophore being selected such that an emission spectrum of the donor chromophore overlaps with an absorption spectrum of the acceptor chromophore.

Abstract: A downhole apparatus for use in a wellbore. The apparatus has a housing that defines a central flow passage and a plurality of ports that extend through a wall of the apparatus and intersect the central flow passage. A tracer material is positioned in at least one of the ports and once positioned in at least one of the ports, the tracer material is exposed to the exterior of the housing and to fluid in the wellbore.

Abstract: A drilling equipment tracking system includes a piece of drilling equipment and a traceability tag coupled to the piece of drilling equipment. The traceability tag has a unique identifier. A mobile device is configured to obtain the unique identifier and access a remote server containing an equipment file corresponding to the piece of drilling equipment based on the unique identifier.

Abstract: A rotating control device includes a housing comprising a bore extending through the housing, a rotating body positioned within the bore of the housing and rotatable with respect to the housing and a packer assembly positioned within the bore of the housing between the housing and the rotating body and configured to form a seal between the housing and the rotating body. The device further includes a transmitter configured to transmit a sensor signal through the packer assembly and a receiver configured to receive the sensor signal from the transmitter through the packer assembly.

Abstract: In one or more embodiments, a method includes positioning an actuator in a wellbore and transmitting, from the actuator, an actuation signal to a sensor coupled to a casing in the wellbore. The method further includes detecting the actuation signal at the sensor and placing the sensor in a different mode of operation in response to detecting the actuation signal.

Abstract: A downhole repeater network timing system for a drilling rig including a drillstring extending subsurface downwardly from a surface wellhead. The system includes a node located at the drillstring lower end and including a sensor adapted for providing a signal data set output corresponding to downhole drilling conditions. Multiple nodes are located downhole between the Bottom Hole Assembly (BHA) and the wellhead and are associated with the drillstring. The nodes are adapted for receiving and transmitting the signals. The timing control system is adapted for controlling all times within a timeframe according to pre-configured constants known to all nodes. A downhole low rate linear repeater network timing method uses the system.

Abstract: A full-duplex borehole communication system includes a single light source to generate a light signal. A downlink modulator is coupled to the light source to modulate the light signal in response to downlink data using a first protocol to generate a first modulated light signal. An uplink modulator is coupled to the downhole modulator to modulate the first modulated light signal in response to uplink data using a second protocol to generate a second modulated light signal. A downlink receiver is coupled to the downlink modulator to demodulate the first modulated signal to recover the downlink data. An uplink receiver is coupled to the uplink modulator and configured to demodulate the second modulated light signal to recover the downlink data and the uplink data. Asymmetric protocols are used between the downhole portion of the system and the uphole portion.

Abstract: A cementing system is provided. A cement slurry dispenser includes at least one control valve, at least one liquid additive pump, and at least one water pump. A computer has a display for an interface screen. The e interface screen displays a list zone of available selectable tests for the cement slurry dispenser and corresponding global selection choices, a detail zone, wherein in response to selection of one of the selectable tests from the list zone, substeps of the selected one of the selectable tests is displayed a local activate button configured to commence only the selected one of the selectable tests displayed in the detail zone; and a global activate button configured to commence all of the selectable tests in the list zone that are indicated as selected by the corresponding global selection choices. The computer implements the tests on the cement slurry dispenser.

Abstract: The present disclosure relates to testing tools that comprises: a cable-head assembly for connecting the testing tool to an end of a length of coiled tubing; a pump assembly comprising a downhole pump; an upper packer-assembly comprising an upper packer-element; a lower packer-assembly comprising a lower packer-element; a sensor assembly comprising one or more sensors with the sensor assembly positioned in fluid communication with a plenum between the upper and lower packer assemblies; and a testing port that is adjacent the sensor assembly. The testing tool is moveable between a first configuration where the upper and lower packer-elements are unset and a second position where the upper and lower packer-elements are set and the testing port is in fluid communication with the downhole pump. Methods of using the testing tools is also described.

Abstract: The present disclosure relates to the hydrocarbon production, in particular to measuring the fracture closure pressure in a formation penetrated by a wellbore using marker agents.

Abstract: A milling device for excavating mining materials is disclosed. The milling device comprises a milling drum rotatable about a drum axis; a first group of excavating heads arranged around a periphery of the milling drum and driven to rotate about a first rotational axis extending substantially radially to the drum axis; and a second group of excavating heads arranged around the periphery of the milling drum and rotatable about a second rotational axis extending substantially radially to the drum axis. The first group of excavating heads includes a plurality of first excavating tools configured to perform a first, cutting operation, and the second group of excavating heads includes a plurality of second excavating tools configured to perform a second excavating operation different from the first, cutting operation.

Abstract: Disclosed is a paired air pressure energy production system and a production method thereof. The paired air pressure energy production system includes a paired air pressure energy storage device, a pneumatic compressor and a power device, The paired air pressure energy storage device includes a high pressure air container and a low pressure air container, the high pressure air container is filled with first gas, and the low pressure air container is filled with second gas; and the power device is connected with a rotating shaft of the pneumatic compressor and used for driving the rotating shaft of the pneumatic compressor to rotate. According to the invention energy in a natural environment is collected by the power device, and is converted into mechanism energy, so as to achieve the aim of producing paired air pressure energy.

Abstract: In order to optimise a compressor, including a compressor housing, a scroll compressor unit that is arranged in the compressor housing and has a first compressor body and a second compressor body that is movable in relation to the first compressor body, an axial guide that supports the movable compressor body to prevent movements in the direction parallel to the centre axis of the stationary compressor body and, in the event of movements, guides it in the direction transverse to the centre axis, parallel to a plane perpendicular to the centre axis, an eccentric drive for the scroll compressor unit, wherein the eccentric drive has an entrainer that is driven by the drive motor, that revolves on a path about the centre axis and that, for its part, cooperates rotatably with an entrainer receptacle in the second compressor body, and a coupling that prevents the second compressor body from rotating freely, it is proposed that the axial guide should have a carrier element, which serves as a base for supporting a co

Abstract: A runner for a hydraulic turbine or pump has a plurality of blades. Each of the blades is defined by a pressure surface, an oppositely facing suction surface, a leading edge and a spaced-apart trailing edge. At least one of the blades has a device for supplying a flow of oxygen containing gas to the trailing edge of the same blade. The device includes at least two separate gas inlet apertures and at least two separate gas passages, each extending from one of the separate gas inlet apertures to a separate group of orifices in the trailing edge of the same blade. Each of the separate group of orifices has at least one orifice to admit gas out of the corresponding separate gas passage to the passing fluid during the operation of the runner.

Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.

Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.

Abstract: A casting core may include a core body and a tip comb extending from a tip region of the core body. The tip comb may be integrally formed with the core body. The tip comb may comprise a first casting pedestal and a second casting pedestal. The first casting pedestal and the second casting pedestal may define an aperture having a tapered geometry.

Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.

Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.

Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.

Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

Abstract: A ceramic matrix composite (CMC) turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region. At least one central CMC ply extending from the root region is interwoven with at least one insert extending toward the narrowed neck region from the hub region. A method of forming a CMC turbine blade includes interweaving at least one central CMC ply extending from the root region with at least one insert extending toward the narrowed neck region from the hub region. The CMC turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region.

Abstract: A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.

Abstract: A coated ceramic matrix composite component and a gas turbine assembly are provided. The coated ceramic matrix composite component comprises a substrate comprising an endface surface and a hot gas path surface. The hot gas path surface is arranged and disposed to contact a hot gas path when the component is installed in the gas turbine assembly. The endface surface is disposed at an endface angle to the hot gas path surface and opposing at least one adjacent component when the component is installed in the gas turbine assembly. The coated ceramic matrix composite component further comprises an environmental barrier coating on at least a portion of the endface surface.

Abstract: A coated ceramic matrix composite or metallic component and a gas turbine assembly is provided. The component comprises a substrate comprising a first surface and a hot gas path surface. The hot gas path surface is arranged and disposed to contact a hot gas flow when the component is installed in the gas turbine. The first surface is disposed at an angle to the hot gas path surface and opposes at least one adjacent component when the component is installed in the gas turbine. The component further comprises an angled or rounded feature extending from the first surface to the hot gas path surface. The component further comprises an environmental barrier coating or thermal barrier coating on at least a portion of the hot gas path surface. The angled or rounded feature reduces an incidence angle of the hot gas flow onto the first surface. The gas turbine assembly comprises a plurality of the coated components.

Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate comprising a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.

Abstract: A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pivot axis that extends radially away from the central axis to vary a pitch of the fan blade. The fan further includes a counterforce system configured to resist forces that urge the fan blades away from their pitch positions during operation of the gas turbine engine.

Abstract: An interlocking shroud assembly for a turbine engine comprising at least two shroud elements, each having confronting radial ends that define a split interface with axial fore, aft, and circumferential portions.

Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.

Abstract: A ring seal assembly includes a first ring seal that is symmetrical with respect to a radially extending plane. A second ring seal is separated axially from the first ring seal by a spring. The second ring seal includes a first inner circumferential surface. An interference feature extends radially inward from the first inner circumferential surface to a second inner circumferential surface.

Abstract: A turbine shroud assembly including an outer shroud arranged within a turbine and further comprising opposed extending portions. The turbine shroud assembly further including an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further including a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The turbine shroud assembly further including at least one of the inner shroud, the outer shroud and the spline seal including at least one protrusion for maintaining positive retention of the spline seal during non-operation of the turbine.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

Abstract: A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.

Abstract: An apparatus and methods for controlling tip clearance in gas turbine engines may be provided. The apparatus and methods may include situating fins on a surface of a turbine case included in a turbine section of the gas turbine engine. The fins may act as a means for maintaining tip clearance by, for example, controlling the thermal expansion of the turbine case. The turbine case may shroud turbine blades, and the turbine blades may include tips at a radial end of the blades. During operation of the gas turbine engine, the clearance between the tips and the turbine case is desirably as small as possible while avoiding contact in order to optimize efficiency of the gas turbine engine.

Abstract: A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.

Abstract: A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane.

Abstract: Methods and apparatus for reducing flow distortion at engine fans of nacelles are disclosed. An example apparatus for reducing flow distortion at an engine fan of a nacelle includes a plurality of nozzles radially spaced about an inner wall of the nacelle. In some examples, respective ones of the nozzles are positioned to eject corresponding respective jets of fluid adjacent the inner wall in a downstream direction toward the engine fan. The example apparatus further includes a controller to selectively activate the respective ones of the nozzles according to a time-based sequence. In some examples, the time-based sequence corresponds to a directional sequence that moves in an arcuate direction along a circumference of the inner wall.

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 nozzle drive mechanism includes: a plurality of nozzle vanes; a plurality of link plates each fixed to a shaft portion of one of the plurality of nozzle vanes; a nozzle ring having an annular main body portion including shaft holes, each of which pivotally supporting a shaft portion of one of the nozzle vanes, the nozzle ring arranged between the link plates and the nozzle vanes; a regulation pin having one end attached to the main body portion of the nozzle ring and the other end protruding from an opposing surface of one of the link plates facing the nozzle ring; and a positioning pin provided separately from the regulation pin and assembled to a wall portion positioned opposite to the nozzle ring across the link plate at a position where the positioning pin is brought into contact when the nozzle ring rotates.

Abstract: The invention relates to a method of monitoring a start-up sequence of a turbomachine that comprises a compressor equipped with a rotor, a starter capable of driving the rotor in rotation and a combustion chamber. The start-up sequence comprises a first phase during which the starter increases the rotation speed of the rotor up to an instant at which fuel is injected into the turbomachine combustion chamber, and a second phase after the first phase that terminates when the starter stops driving the rotor. The method includes: acquisition (ACQ) of a signal representative of the rotation speed of the rotor during the start sequence; detection (DRP1, DRP2, INT) of an instant at which there is a sudden change in the variation of said signal with time, the sudden change instant thus detected being deemed to be the instant at which an air-fuel mix is ignited in the combustion chamber.

Abstract: An emergency wind turbine system for an aircraft including an outer structure in which an opening is made includes an emergency wind turbine including: a mast; a turbine including a body mounted on the mast that rotates about an axis of rotation, and a single blade or two blades extending radially from the body between a blade root and a blade head; a locking device to lock rotation of the turbine body about the axis of rotation, when the emergency wind turbine moves between retracted and deployed positions, such that the blade root axis forms an acute locking angle with an orthogonal projection of the longitudinal axis of the mast over a plane substantially perpendicular to the axis of rotation of the turbine and in which the blade root axis extends, to reduce the volume swept by the turbine when it moves between the retracted and deployed positions.

Abstract: A device for cleaning blades in a turbomachine is disclosed. The device may include a frame, a cleaning jaw pivotably attached to the frame, opposing cleaning pads attached to a distal end of the cleaning jaw, a cleaning pad actuator attached to the frame for actuating the opposing cleaning pads, and at least one handle attached to the frame.

Abstract: A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

Abstract: A turbine shroud assembly is disclosed including an inner shroud, an outer shroud, a shroud dampening pin, and a biasing apparatus. The inner shroud is adjacent to a hot gas path. The outer shroud is adjacent to the inner shroud and distal from the hot gas path, and includes a channel extending from an aperture adjacent to the inner shroud. The shroud dampening pin is within the channel and contacts the inner shroud, and includes a shaft, a contact surface, and a cap. The shaft is within the channel. The contact surface extends through the aperture in contact with the inner shroud. The cap is distal across the shaft from the contact surface. The biasing apparatus contacts the cap, is driven by a pressurized fluid, and provides a biasing force away from the outer shroud along the shroud dampening pin to the inner shroud through the contact surface.