Abstract: A modular ‘Subsea Level Gas Separator of Oil Well Effluent’ (SLGOE) about the well-head, precludes gas entrainment reaching the rig. The effluent, past the well-head BOP, through ab oil-diversion tube, enters into ‘gas-separator’ tanks, creating fountain-like up-flow (Sumathi Paturu Up-flow Model). The oil down-streaming into an ‘oil-passage tank’, is ‘styphoned’ to the partitioned collection system, past the diversion tube. Massively clustered top outlets of the tanks let off the ‘instantly’ rising gases. In another embodiment otherwise similarly configured, the oil flows down from the top to the bottom of the tank (Symathi Paturu Down-flow Model). In either model, a gas entrainment instantly reaching the top of the tank(s) is precluded to entrain into the down-streaming oil. Additionally, the immensely pressured gases are attenuated by enormous receptive volume of the tanks and the multiple upstream gas-outlets.

Abstract: A downhole intelligent reamer controller detects the difference between rotary drilling and sliding drilling, responds appropriately and quickly to multiple changes between rotary drilling and sliding drilling that may occur several times each stand of pipe. Additional controls prevent deployment of reamer members at inappropriate times such as when drilling out cement, testing, and running in and out of the wellbore. In one embodiment, a separate modular control sub is disclosed that may be utilized with and/or removably secured to an expandable reamer and/or other types of downhole tools.

Abstract: An apparatus and method may operate to mount one or more communication assemblies relative to the exterior of a casing being placed in a borehole. Two communication assemblies can be placed in longitudinally spaced relation to one another along the casing, wherein each communication assembly is configured to obtain excitation responses from electrodes of a fluid sensing component, where the excitation responses vary based on properties of fluids in one or more regions of the annulus surrounding the casing. Additional apparatus, systems, and methods are disclosed.

Abstract: An apparatus for protecting a module used in a borehole may include a plurality of shock protection elements associated with the module. The plurality of shock protection elements cooperatively has a macroscopic non-linear spring response to an applied shock event. The plurality of shock protection elements may include at least an enclosure and a dampener connecting the module with the enclosure. A related method for protecting a module used in a borehole may include enclosing the module within the plurality of shock protection elements; disposing the module in the borehole; and subjecting the module to a shock event. The plurality of shock protection elements cooperatively has a macroscopic non-linear spring response to the shock event.

Abstract: Disclosed embodiments include well ranging apparatus, systems, and methods which operate to measure electromagnetic field strength components associated with an electromagnetic field originating at a first well, via direct transmission or backscatter transmission, using at least one ranging electromagnetic field strength sensor attached to a housing, to provide ranging measurements. Further activities may include obtaining distorting field strength measurements using one or more reference electromagnetic field strength sensors, which may form or be attached in a closed loop path around the housing; and determining an approximate range between the first well and a second well in which the ranging electromagnetic field strength sensors are disposed, based on the ranging measurements and the distorting field strength measurements. Additional apparatus, systems, and methods are disclosed.

Abstract: Various embodiments disclosed relate to methods and apparatuses for determining a minimum miscibility pressure of a fluid with and oil composition. In various embodiments, the method can include placing a fluid into a pressure chamber at a first pressure. The pressure chamber can include at least one capillary tube having one end disposed in an oil composition in the pressure chamber. The fluid can include at least one of a gas, a liquid, and a supercritical fluid. The method can include measuring a height of the oil composition in at least one of the capillary tubes. The method can include repeating the measuring for at least one cycle using a second pressure different than the first pressure. The method can include determining the minimum miscibility pressure of the oil composition with the fluid by extrapolating from the two or more measurements.

Abstract: An example method includes introducing a string of tubing into a wellbore to perform a primary operation, the string of tubing including at least one sensor for measuring strain and at least one device operatively associated with the at least one sensor. The method further includes translating the string of tubing relative to the wellbore, imparting a load on the string of tubing when the tubing becomes stuck in the wellbore at a stuck point, and thereby generating strain in the string of tubing above the stuck point. Additionally, the method includes measuring the strain with the at least one sensor, transmitting data indicative of the strain to a surface location with the at least one device, and determining a position of the at least one sensor in the wellbore, as based on the strain, relative to the stuck point.

Abstract: A gas analyzer system that can detect atmospheric air gasses in drilling mud is used to calculate an actual lag time in a well. The calculated lag time and a theoretical lag time may be compared to estimate a caving percentage in an open hole section of the well.

Abstract: Systems and methods for monitoring a condition of a tubular configured to convey a fluid such as for use in producing hydrocarbons in relationship with a hydrocarbon system related wellbore operation. The methods include transmitting a data signal along the tubular with the communication network. The methods may include initiating a tubular operation responsive to the data signal indicating that the condition of the tubular is outside a predetermined condition range. The methods may include transmitting the data signal by propagating the data signal along the tubular via a plurality of node-to-node communications between communication nodes of the communication network and monitoring a signal propagation property of the plurality of node-to-node communications that is indicative of the condition of the tubular. The methods may include detecting the condition of the tubular and generating a condition indication signal.

Abstract: A subsea electronic information system for managing data related to a characteristic of subsea equipment locatable subsea. The system includes sensors locatable subsea and in communication with and capable of measuring a characteristic of the subsea equipment. A sensor interface box (SIB) separate from the sensors and locatable subsea includes a processor and a memory device capable of receiving and storing sensor measurement data. Additionally, the SIB is in data and power communication with the sensors. The system further includes a subsea retrievable data capsule capable of recording all system data over a long period. The capsule may be recovered from subsea (independently of the other elements of the information system) for forensic analysis of the recorded data.

Abstract: Systems and methods for communicating messages over a three-phase power cable between surface equipment and downhole equipment in a well. A transmitter parses messages into data bit pairs and generates a parity bit for each pair (a triplet). The bits of each triplet are concurrently but separately transmitted over the power cable. Each triplet is received from the power cable by a receiver and is decoded to identify the data bits. The receiver may verify the received bits and/or recover a lost bit in each triplet. The data bits are then reconstructed into the original message. Since each triplet has two bits, the effective data rate is twice the data rate of transmitting a single bit at a time. The parity bit enables recovery of data with a bit error rate of up to 1 in 3.

Abstract: An actuator for a mud pulse telemetry tool. The actuator includes a solenoid-based servo valve with a coil shaft responsive to data transmitted by a data processor. The coil shaft is movable between an extended position and a retracted position. Movement of the coil shaft to the extended position moves a poppet to close a servo orifice thereby preventing mud flow to a main mud pulse valve of the mud pulse telemetry tool. Movement of the coil shaft to the retracted position moves the poppet to open the servo orifice thereby allowing mud flow to actuate the main mud pulse valve. The poppet is connected to a poppet shaft and the poppet shaft cooperates with the coil shaft in a slide hammer mechanism to amplify force provided by the coil shaft against the poppet shaft with linear movement of the coil shaft to the extended position and to the retracted position.

Abstract: In one aspect, an apparatus for use in a drilling assembly is disclosed that in one embodiment includes a flow control device that further includes: a fluid flow path having an inlet and an outlet; an electromagnetic circuit that includes a closing member made from a soft magnetic or magnetic material as a part of the electromagnetic circuit, wherein the closing member moves from a first open position to a second closed position to close the fluid flow path to produce a pressure pulse in a fluid flowing through the fluid flow path when the electromagnetic circuit is formed.

Abstract: Selecting hydrocarbon wells for well testing. The selecting may include identifying hydrocarbon wells whose last well test took place prior to a predetermined date; identifying hydrocarbon wells with a parameter that exceeds a predetermined threshold; and selecting a predetermined number of hydrocarbon wells from the wells identified.

Abstract: Improved bit holder/bit holder block structure provides increased access to the rear of the assembly allowing bit holder blocks to be mounted closer to each other for micro-milling operations. Shortened bit holder shanks are reconfigured from prior art to provide increased holding power between the bit holder shank and bit holder block bore.

Abstract: The invention relates to a hydraulic axial piston machine (1) of dry case type of construction, whose case (2) is provided for connection to a gearing case (21) so as to form a fluid-tight overall case. The case (2) has openings (10) which permit the passage of leakage hydraulic fluid or of lubricant into the gearing case (21). By means of this design, splashing losses of the axial piston machine (1) are eliminated, and the leakage hydraulic fluid or the lubricant serve for the lubrication both of the axial piston machine (1) and of the gearing (20).

Abstract: A spring return apparatus for elastically prestressing sliding pads against a sliding bearing face of an axial piston machine. The sliding pads are positioned on working pistons mounted axially movably in cylinders of a cylinder barrel that drives a drive shaft including a spring plate and a supporting plate. The spring plate includes a ring region surrounding a central opening, and levers extending radially from the ring region. The levers are arranged spaced apart or distributed uniformly in the circumferential direction, and are elastically flexible and/or elastically pivotable in the axial direction. Every two adjacent levers delimit a receiving region for receiving a tapered section of a working piston or a sliding pad. The supporting plate has a circular ring-shaped supporting region configured to support radially outer end sections of the levers if the supporting plate is arranged concentrically with respect to and axially adjacently to the spring plate.

Abstract: A transmission assembly for a rotary piston and cylinder device, comprising a first gear (120) and a gear sub-assembly (15, 16, 17, 18, 19), the first gear connectable to a rotatably mounted shutter (12) of the device, and the first gear extending from a side of the shutter, and the first gear connected to the gear sub-assembly which converts rotation to an axis of rotation different to that of the shutter.

Abstract: A laser net shape manufactured BLISK, compressor blade, turbine blade or turbine component including a plurality of overlapping predetermined variable bead widths of a material defining a first material layer, a plurality of overlapping predetermined variable bead widths of a material deposited on top of the first material layer, forming a second material layer; and additional material layers deposited on top of the first material layer and the second material layer. The variable bead width of the deposited material is controlled to maintain the approximately constant percent of bead width overlap. A first 2 to 100 deposited powder layers are deposited by a first laser power and the remaining powder layers are deposited by a laser power that is ramped down over the course of depositing the remaining powder layers. In addition, disclosed is A BLISK, compressor blade, turbine blade or turbine component formed by a method.

Abstract: Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or treated turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface is oriented along a second axis substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.

Abstract: A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.

Abstract: A blank casting for producing a turbine engine rotor blade, with a vane connected by a platform to a root, is provided. The root has an axial machining allowance intended to be removed by machining from each of its axial extremities. At least one of the axial extremities of the root includes at least one transverse channel that extends over the entire transverse width of the root and whose depth is greater than the machining allowance. A process for obtaining the blade by machining this blank casting is also provided.

Abstract: A method is provided for designing an airfoil. The method includes considering a baseline airfoil having a first camber distribution and a first aerodynamic efficiency; reducing the first camber distribution to result in a reduced camber airfoil with a second camber distribution and a second aerodynamic efficiency such that the second aerodynamic efficiency is approximately equal to the first aerodynamic efficiency; and producing the airfoil with the second camber distribution.

Abstract: Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).

Abstract: A rotor blade with a supporting structure, wherein the rotor blade has a rotor blade base section and a rotor blade tip section, is provided. The supporting structure includes a first supporting segment for supporting the rotor blade base section and at least a second supporting segment for supporting the rotor blade tip section. Furthermore, the supporting structure includes the first supporting segment and the second supporting segment along the rotor blade longitudinal direction. The first supporting segment is joined to the second supporting segment in a supporting structure transition section, wherein the supporting structure transition section is located in between the rotor blade base section and the rotor blade tip section. Finally, the first supporting segment and/or the second supporting segment include a fiber material. A method for manufacturing the rotor blade is also provided.

Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring.

Abstract: A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem.

Abstract: A turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

Abstract: A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.

Abstract: A damper system for a turbine having adjacent turbine bucket platforms including opposing slash faces having opposing grooves is provided. The system includes a pin having a substantially cylindrical-shaped body configured for positioning in the opposing grooves. A set of slots are provided in an outer surface of the pin and at spaced axial locations therealong. The set of slots face in a radially outward direction relative to the turbine bucket platforms.

Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.

Abstract: A turbine blade comprises an airfoil. An outer shroud at a tip of the airfoil, has a main surface facing the airfoil and forming a first plateau. A gusset or gussets have a periphery raising from the main surface, and a second plateau between the periphery and the airfoil. A gas turbine engine with such turbine blade is also provided.

Abstract: An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network.

Abstract: A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection.

Abstract: Provided are a stator blade assembly advantageous for improving the evacuation performance by shortening the evacuation time, and an exhaust pump provided with such a stator blade assembly. Inner and outer stator blade bases of a plurality of stator blades are supported by frames. A projecting portion protruding from the frame supporting the inner stator blade base, or from the frame supporting the outer stator blade base, or from both of the frames is provided in a gap in the vicinity of the inner or outer stator blade base between one of the supported stator blades and the stator blade transversely adjacent thereto.

Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.

Abstract: Respective seals (54, 78) for the upper and lower spans (48A, 48B) of an exit frame (48) of a turbine combustion system transition piece (28). Each seal has a first strip (55, 79) and a second strip (66, 88) of a sealing material. The two strips of each seal are attached together along a common edge. The second strip is flexible, generally parallel to the first strip, and has a bead (72, 90) along its free edge. This forms a spring clamp that clamps a rail (68, 86) of the exit frame between the bead and the first strip of each seal. A tab extends axially aft from the first strip of each seal for insertion into a circumferential slot (58, 82) in a turbine inlet support structure (52, 76), thus sealing the transition piece (46) to the turbine inlet for efficient turbine operation.

Abstract: An air seal for a gas turbine engine platform comprises a flow path platform, a seal retention ring, a finger seal. The seal retention ring is situated radially adjacent the flow path platform. The finger seal is retained by the seal retention ring between the flow path platform and the seal retention ring. The finger seal comprises a first ply with first keyhole slots, a second ply with second keyhole slots circumferentially offset relative to the first keyhole slots, and a foil layer. The foil layer is disposed between the first and second plies. The finger seal has a series of cooling holes in the outer circumferential segment to cool the outer diameter of the seal. In addition, leakage between the finger seal and the flow path platform cools the inner diameter of the seal.

Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.

Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

Abstract: A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other.

Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.

Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.

Abstract: A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud (120) and an outer shroud, with vanes (124) extending between them, the radially inner ends of the vanes being engaged with clearance (125) in orifices in the inner shroud and being secured to the inner shroud by means of a polymerizable sealing resin (126), the guide-vane stage being characterized in that a gasket (140) is mounted on the radially inner end of each vane, the gasket including a slit through which the vane passes and bearing against the radially inside surface of the shroud or in the proximity of said surface, in order to limit the passage of resin through the above-mentioned clearance while the resin is being applied to the inside surface of the shroud.

Abstract: A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.

Abstract: A compressor rectifier of a turbomachine including a plurality of stationary blades extending in a circular fashion between an inner shroud and an outer shroud that are concentric and define interblade channels forming an air duct in which air to be compressed flows, the inner shroud including at least one vortex generator extending into the air duct to reduce corner vortices. The vortex generator is positioned axially in the interblade channel, between the axial position of a leading edge of the blades and those of a trailing edge thereof.

Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.

Abstract: A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path.