Abstract: Systems and methods are provided for using opto-electrical networks to control downhole electronic devices. A system is provided that can include an optical transmitter. The optical transmitter can generate a first electrical signal associated with a radio frequency or a frequency bandwidth of the radio frequency. The optical transmitter can also convert the first electrical signal to an optical signal. The optical transmitter can further transmit the optical signal over a fiber-optic cable to an optical receiver deployed in a wellbore. The system can include the optical receiver. The optical receiver can convert the optical signal to a second electrical signal associated with the radio frequency or the frequency bandwidth. The optical receiver can also control an electronic device in the wellbore that is identified from the radio frequency or the frequency bandwidth of the second electrical signal.

Abstract: Methods for determining the hardness and/or ductility of a material by compression of the material are provided as a first aspect of the invention. Typically, compression is performed on multiple sides of a geologic material sample in a contemporaneous manner. Devices and systems for performing such methods also are provided. These methods, devices, and systems can be combined with additional methods, devices, and systems of the invention that provide for the analysis of compounds contained in such samples, which can indicate the presence of valuable materials, such as petroleum-associated hydrocarbons. Alternatively, these additional methods, devices, and systems can also stand independently of the methods, devices, and systems for analyzing ductility and/or hardness of materials.

Abstract: A method for determining one or more parameters of a formation fracture comprises injecting a viscous fluid in the formation via a flow path; measuring pressure at a location along the flow path; and calculating one or more parameters of a formation fracture based on the measured pressure. The method may permit improved and/or more efficient planning, design and/or performance of, e.g. conformance treatment of the formation fracture.

Abstract: A fluid analyzer for a downhole tool positionable in a wellbore penetrating a subterranean formation is provided. The fluid analyzer includes an optical sensor positioned in the downhole tool to receive a downhole fluid therefrom. The optical sensor includes an optical cell to measure properties of the downhole fluid in a flowline of the downhole tool, and has a wavelength range. The fluid analyzer also includes a calibration fluid having a liquid that absorbs outside of the wavelength range, and a calibrator. The calibrator includes a fluid source housing the calibration fluid and at least one valve. The fluid source is operatively connectable to the optical sensor to provide the calibration fluid thereto whereby the calibration fluid is measureable by and calibratable to the optical sensor.

Abstract: A system includes a formation sampling tool having a body, a probe shoe extendibly mounted to the body, a packer coupled to the probe shoe, and an inlet fixedly coupled to the probe shoe and the packer. The packer surrounds the inlet and the inlet includes an anti-extrusion ring extending beyond an outer surface of the packer. The system also includes a filter disposed within the inlet.

Abstract: A cutter assembly for an undercutting machine for cutting a rock workface and a method of assembling a cutter assembly is provided. The cutter assembly includes a shaft mountable on the machine with one end extending from the machine, and a cutter device arranged in connection to the extended end of the shaft. The cutter device is connected releasably and rotationally rigid to the shaft with a locking arrangement. The locking arrangement includes a first locking device arranged to transfer substantially axial loads, and a second locking device arranged to transfer substantially radial loads.

Abstract: The present invention relates to a pick, in particular, a round shaft pick, having a pick head and a pick shaft, having a support element which has a centring lug on the underside thereof, wherein the centring lug has a centring surface which extends inclined with respect to the central longitudinal axis of the pick and merges into a seat surface. To this end circumferential channel according to the present invention is disposed in the transition region from the centring surface to the seat surface and the depth of the channel relative to the seat surface is greater than or equal to 0.3 mm. The pick has an optimised rotatability and thus a low wear.

Abstract: A combination bit and bit holder assembly includes a bit holder having a forward body portion and a shank. The forward body portion includes an upper end and a lower end. An insert is mounted in the bore of the upper end of the body portion. The insert also includes a central bore that receivingly retains a receiving cup. The receiving cup includes a bottom portion and an annular flange that extends from the bottom portion and defines a hollow forward portion. A bit is mounted in the hollow forward portion of the receiving cup which is configured to have a ductility that provides impact absorption to the bit.

Abstract: A mine control system for monitoring mine operations includes a plurality of mine vehicles provided with on-board monitoring means. Monitoring data is transmitted from the mine vehicle to the mine control system, which is provided with a mine plan. The mine control unit is configured to compare the received monitoring data with the mine plan and to determine the current state of the mine relative to the mine plan on the basis of the monitoring data.

Abstract: A deep sea mining method includes providing a deep sea mining system for mining matter from a bottom of a body of water, the mining system including: a slurry line coupled with a pump system to transport the slurry from the bottom of the body of water; and a return line in fluid communication with the slurry line and distinguishable from the slurry riser, for transporting non valuable slurry part to the bottom of the body of water, the return line having a return line outlet proximate the bottom. The deep sea mining method further includes spreading the non valuable slurry part over the bottom of the body of water in a controlled manner.

Abstract: A shield-carried noncontact frequency-domain electrical real-time advanced detection system and method are provided. Noncontact electrodes are installed on a cutter head of a shield tunneling machine, current is emitted and received using capacitance coupling, the electrodes are connected to a host via a multi-way swivel joint, measured data is inversed and interpreted in real time, and the prediction result is transmitted to a control system of the shield tunneling machine so as to provide a technical support for safety construction of the shield tunneling machine; the noncontact electrodes are installed on the shield cutter head. Real-time advanced detection of geology in front of a tunnel face can be realized in the tunneling process, so that the requirement for quick tunneling construction is met, and the efficiency of advanced geological detection of the shield tunneling machine is improved; and an electrode system is only installed on the cutter head.

Abstract: An engine includes a housing defining an annular bore and a piston assembly disposed within the annular bore. The engine includes a rotary valve comprising a loop-shaped wall structure defining an opening substantially perpendicular to an axis of rotation of the loop-shaped wall structure. A portion of the rotary valve is disposed within the annular bore such that the axis of rotation of the loop-shaped wall structure is substantially perpendicular to an axis of rotation of the piston assembly. The engine includes a rotary drive mechanism connected to the rotary valve and configured to rotate the rotary valve between a first position to align the opening of the loop-shaped wall structure with the annular bore to allow a piston of the piston assembly to travel within the annular bore and a second position to define a combustion chamber relative to the piston of the piston assembly at the second location.

Abstract: The technical field of the invention is steam turbines including a steam feed circuit based on a functional steam generator set that may be nuclear- or fossil-fuel powered, and in particular a steam feed circuit (1) of a turbine (2), comprising n main steam lines (3) and n? steam admission lines (4) to the turbine, the number n? of steam admission lines (4) to the turbine being strictly greater than the number n of main steam lines (3), characterized in that there are n direct steam admission lines (5) to the turbine linking the as main steam lines (3) directly to the steam admission lines (4) to the turbine.

Abstract: A compressor of an axial turbine engine comprising two rotors or contra-rotating drums, of which an inner rotor and an outer rotor are each provided with blade rows forming a regular alternating pattern. The inner rotor is provided with a radial annular junction fixed to the transmission shaft coming from a turbine. The outer rotor surrounds the inner rotor. The compressor also comprises a rotating bearing linked to the outer rotor and arranged axially level with the radial junction of the inner rotor so as to align the mechanical links axially. This alignment limits the effect of centrifugal force between the clearances between the blades and the walls of the rotors. A transmission with a pinion with a radial rotation axis allows the outer rotor to be driven by the inner rotor.

Abstract: The disclosure provides a turbine blade. A turbine blade includes a shroud at a tip of the blade and an airfoil having a leading edge extending between the shroud and a root of the blade; a cutout portion extending at least along the leading edge of the airfoil nearest the shroud; an insert welded to the cutout portion at a weld region; and a weld-free region located between the insert and the cutout portion nearest the shroud.

Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.

Abstract: An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.

Abstract: A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings (80) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.

Abstract: A component includes a structural member and an outer wall covering the structural member with a gap between the outer wall and the structural member. The outer wall includes an array of holes, each of the array of holes extending from an exterior surface of the outer wall to an interior surface of the outer wall. The outer wall includes an array of recesses on the interior surface of the outer wall, each hole in the array of holes terminating within one of the array of recesses of the outer wall.

Abstract: A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Abstract: The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures. A duct plate encloses the first portion of the impingement plate. The duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures. Compressed air from the outer chamber flows through the one or more impingement apertures into the inner chamber and exits the inner chamber through the one or more post-impingement apertures.

Abstract: It is an objective of the invention to provide a steam turbine rotor of which a rotor shaft is made of a low-cost heat resistant ferritic steel and that can withstand high main steam temperatures of about 650° C. There is provided a steam turbine rotor comprising: a rotor shaft made of a heat resistant ferritic steel such as a 12-Cr steel; and a rotor blade made of a Ti—Al alloy, wherein the Ti—Al alloy includes: from 38 to 45 atomic % of Al; from 0.5 to 2 atomic % of V; from 2 to 6 atomic % of Cr and/or Mo; and the balance being Ti and incidental impurities.

Abstract: A process of producing a ceramic matrix composite component. The process includes positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein. At least a portion of the cavity includes a terminal diameter sufficiently small to permit infiltration of a densifying material. The plurality of ceramic matrix composite plies are densified to form a densified body. The densifying results in the portion of the cavity including the terminal diameter being filled with densifying material and the cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

Abstract: A vane for an exhaust system duct in a gas turbine engine including a vane plate, a guide plate, and a baffle. The vane plate includes a leading edge, a first leg and a second leg, with the first and second legs respectively extending on opposing sides of the leading edge to form a substantially U-shaped profile. The baffle connects respective distal ends of the first and second legs. The guide plate is accommodated within the vane plate, and includes a first aperture extending along the guide plate and aligned with the leading edge. The vane further includes a fluid inlet arranged, in use, to direct a fluid flow from outside the duct into an interior of the vane.

Abstract: A turbomachine includes a plurality of transition ducts and a support ring assembly. The outlet of a transition duct includes an inner flange and an outer flange. The turbomachine includes bore holes defined in the inner flange and outer flange, mating bore holes defined in the support ring assembly, and mechanical fasteners connecting the inner flange and the outer flange to the support ring assembly. A first one of the bore holes or mating bore holes has a first maximum radial gap and a first maximum tangential gap relative to an associated mechanical fastener. A second one of the bore holes or mating bore holes has a second maximum radial gap and a second maximum tangential gap relative to an associated mechanical fastener. The second maximum radial gap is greater than the first maximum radial gap or the second maximum tangential gap is greater than the first maximum tangential gap.

Abstract: The invention relates to a turbomachine vane comprising a root and a blade including a median main plane having a longitudinal and radial main orientation, which is carried by the root, the blade including a leading edge located at an upstream longitudinal end, a trailing edge located at a longitudinal end downstream of the leading edge with respect to a gas stream flowing around the blade, a lower surface wall and an upper surface wall which are located laterally remote from each other and each connecting the leading edge to the trailing edge, and a top located at the free outer radial end of the blade, the blade further including a fin having a longitudinal main orientation which is carried by the lower surface side, which is located at the top of the blade, wherein the fin is radially inwardly offset with respect to the top of the blade.

Abstract: A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.

Abstract: Aspects of the disclosure include a sealing insert, turbine component, and code for manufacturing a sealing insert. A sealing insert includes at least one insert wall for insertion proximate a component wall to define a space between the at least one insert wall and the component wall. At least one compressible seal is provided between the at least one insert wall and the component wall. The compressible seal or seals divide the space into a plurality of compartments.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: The turbo machine includes a rotor 1 with a rotating shaft 3, a stator 2 enclosing the rotor 1 and a sealing device 20 installed in a clearance passage defined between the rotor 1 and the stator 2, the sealing device 20 controlling a leakage flow from the clearance passage B. The sealing device 20 includes a plurality of sealing fins 24 disposed on at least one of the rotor 1 and the stator 2, and arranged in an axial direction of the rotor 1. The sealing device 20 further includes at least one deceleration controlling member 25 provided on the rotational side. The deceleration controlling member 25 projects toward a chamber 30 defined between the sealing fins 24 and is configured to control a reduction in the velocity of the leakage flow B in the chamber 30 in the rotational direction of the rotor 1.

Abstract: A power transmission for a turbine or a compressor has a housing, a first shaft rotatably mounted so as to be rotatable in one direction in the housing, a barrel rotatably mounted so as to be rotatable in a direction opposite to that of the first shaft within the housing, a first plurality of blades affixed to the first shaft and extending radially outwardly therefrom, and a second plurality of blades affixed to the barrel and extending inwardly therefrom. Each blade of the second plurality of blades is interposed between adjacent blades of the first plurality of blades. A second shaft is mounted exterior of the housing so as to drive the barrel in rotation.

Abstract: A method for starting a combustion system having a first ignition device and an at least second ignition device, a processing unit and a sensor system. To obtain a reliable ignition the method includes as a starting sequence at least the following: monitoring during a working condition of the combustion system, an operational state of the first and the at least second ignition device by the sensor system; identifying a predefined state of the first and/or the at least second ignition device by the processing unit; and as a further step: in case of an identification of the predefined state changing in at least one parameter of at least one of the ignition devices by the processing unit. A combustion system is equipped to be operable with the method as well as to a flow engine with such a combustion system.

Abstract: Apparatus to enable rotation of a compressor, the apparatus comprising: a guide for insertion through a fan of a gas turbine engine to the compressor, the guide including: a surface arranged to guide a drive assembly through an interior portion of the gas turbine engine to the compressor; and a first fastener arranged to fasten the guide to the gas turbine engine.

Abstract: An article, for example a turbomachinery article is presented. The article includes a weldable first component having a base portion and a flange portion. The flange portion is outwardly projecting normal to a surface of the base portion; and is joined with the base portion by a solid state joint. The base portion comprises a nanostructured ferritic alloy; and the flange portion comprises a steel substantially free of oxide nanofeatures. The first component is joined to a second component through the flange portion of the first component by a weld joint.

Abstract: A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, and circulating the anti-icing airflow away from the bypass flow path. Also, an assembly located at least in part inside a turbofan engine and including a heat exchanger, a flow mixing device having a first inlet in the bypass flow path, a second inlet and an outlet, a first conduit providing fluid communication between the heat exchanger and a compressed air portion of the core flow path, a second conduit providing fluid communication between the heat exchanger and the second inlet, and a third conduit in fluid communication with the outlet.

Abstract: A vibration damping assembly and a method of damping vibration in a gas turbine engine are disclosed. The vibration damping assembly includes a strut configured to couple a fan case and turbine engine case of a turbine engine, a strut cavity disposed within the strut, and vibration damping media disposed in the strut cavity.

Abstract: A gas turbine engine is disclosed having a working fluid system capable of moving a working fluid. The working fluid system includes a flow splitter capable of splitting the working fluid into different streams. In one form the flow splitter member is a T-shape, but other embodiments can take on other shapes. The flow splitter can include an internal scoop used to split the flow. In one form internal scoop is annular in shape and includes a turn to direct a split flow.

Abstract: A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

Abstract: A rack for holding a portion of a thrust reverser. The rack may include a base and a supporting frame disposed perpendicularly with the base. The base and the supporting frame may include a hinge at each location where the base and the supporting frame are coupled together. The rack may also include two supporting poles parallel to the supporting frame. The two supporting poles may be designed such that the portion of the thrust reverser may be mounted onto the two supporting poles.

Abstract: A compliant mounting adapter for mounting an engine to a test stand includes: a body having: a first mounting interface configured for being coupled to the test stand; a second mounting interface configured for being coupled to the engine, the second mounting interface spaced-away from the first mounting interface; and a spanning element interconnecting the first and second mounting interfaces. The body is sufficiently flexible so as to permit movement relative movement of the two mounting interfaces, in response to forces generated by engine operation, in at least two degrees of freedom, and has a predetermined stiffness in each of the at least two degrees of freedom, with the predetermined stiffness of each degree of freedom being substantially independent from the stiffness of the other degrees of freedom.

Abstract: In some aspects, a steam turbine system includes a high-pressure turbine section; a low-pressure turbine section; a high-pressure control valve operable to provide an adjustable flow of steam into the high-pressure turbine section; a low-pressure control valve operable to provide an adjustable flow of steam into the low-pressure turbine section; a controller associated with the high-pressure control valve and the low-pressure control valve. The controller is operable to: receive measurements of three or more different operating points of the steam turbine system, the measurements of each of the three or more different operating points including a position of the high-pressure control valve, a position of the low-pressure control valve, and two of process variables of the steam turbine system; calculate coefficients of a steam performance map of the steam turbine system based on the measurements; and generate the steam performance map based on the coefficients.

Abstract: A system for controlling fluid flow in a turbine that includes at least one flow valve configured to regulate fluid intake through the turbine. The system further includes a control system operatively coupled to the at least one flow valve. The control system includes at least one processor configured to receive a percent value flow command. Convert the percent value flow command to a unit value flow command. Determine a unit value stroke command based on the unit value flow command. The processor is further configured to control a position of the at least one flow valve to the unit value stroke command.

Abstract: The present invention provides a method of operating an engine (14) having one or more cylinders (16) each having a piston (18) within the cylinder (16) and each piston (18) having an expansion stroke and a return stroke and a top dead center (TDC) position and a bottom dead center position (BDC) and said engine (14) employing a working fluid (WF) and a heat exchange fluid (HEF), comprising the steps of: introducing the HEF during the return stroke of the engine; introducing the working fluid (WF) during the expansion stroke of the engine; causing the exhaust valve to be opened at or near bottom dead center of the piston BDC; delivering the HEF to the cylinder (16) after the exhaust valve has been opened; and closing the exhaust valve before TDC, such as to allow the working fluid to be compressed by the piston within the cylinder. The invention also provides an engine (14) capable of being operated in accordance with the method.

Abstract: The invention relates to a locking device for a switchable valve drive component, including a first locking body and a second locking body which can be brought into engagement with one another or out of engagement in order to couple to one another or to uncouple two component parts arranged movably with respect to one another, wherein at least one of the two locking bodies has at least one curved surface. In order to increase the wear resistance of the locking device, provision is made for at least one of the two locking bodies to have a plurality of curved surfaces of which the respective curvature is described by radii of identical length having constructional center points spaced apart from one another.

Abstract: A variable valve mechanism includes a rocker arm including a first input arm, a second input arm, and an output arm, and a switch device that switches an operating state to a first state by coupling only the first input arm to the output arm, and switches the operating state to a second state by coupling only the second input arm to the output arm. The switch device includes two pins that are displaceably placed in the rocker arm and contact each other at their end faces, and a displacement device that switches the operating state to the first state by displacing a contact portion between the two pins to between the output arm and the second input arm, and switches the operating state to the second state by displacing the contact portion between the two pins to between the output arm and the first input arm.

Abstract: A valve bridge assembly includes a valve bridge; a first cavity formed towards a first end portion of the valve bridge; and a hydraulic lash adjuster (HLA) disposed within the first cavity for engaging a first valve stem. The HLA includes a first contact surface for engaging the first valve stem. The first contact surface is curved.

Abstract: A control valve for a camshaft adjuster having a valve housing (3) and having a control piston (4) which is guided axially movably in a receptacle of the valve housing (3), and having a check valve (2) which is arranged within the piston cavity (22) and consists of a spring band (23) with overlapping ends which is wound to form a cylindrical valve spring, wherein the spring band (23), at the inner end (24) thereof, merges into an axially extending spacer element (28), the axial ends (29, 30) of which may be brought into contact with the inner side of the end surfaces of the control piston (4) is provided. The spacer element (28) has a uniform surface which is interrupted in an axial section of the spacer element (28) by way of an elevation (32).

Abstract: A valve timing regulation device includes a housing, a vane rotor, a sleeve and a spool. The housing is fit to an end of a camshaft. The sleeve has a supply port, a drain port, a first control port, a second control port and a first drain oil passage. The spool has a connection oil passage provided to a shaft center part to connect the supply port to either the first control port or the second control port according to an own axial position. The drain port is connected to a drain space through a second drain oil passage provided to span the vane rotor and the camshaft. A hydraulic oil of a retard chamber is discharged to the drain space through the second drain oil passage. It is unnecessary to provide a discharge hole to the camshaft, and a shaft length of the camshaft can be shorter.