Abstract: An assembly for use in a wellbore can include a plurality of sensors positioned external to a casing string. The plurality of sensors can be positioned for detecting an amount of a hydrocarbon that is present in a fluid in the wellbore and a pH of the fluid in the wellbore. The plurality of sensors can be positioned for wirelessly transmitting signals representing the amount of the hydrocarbon that is present in the fluid and the pH of the fluid to a receiving device.

Abstract: An improved rotating cutting bit used in a road resurfacing machine, wherein the cutting bit includes a metal shank and having a forward end, and wherein the forward end includes a bore or recess that is adapted to fixedly receive at least a portion of a point attack insert. The improvement comprises a head section; an axially aligned transitional intermediate section contiguous with the head section having a first diameter, d, and a sectional height, H1; and an axially aligned base section adjacent to the intermediate section having a second diameter, D; wherein d:H1 is greater than 1.0, the ratio of d:D is from 0.62 to 0.68, wherein the point attack insert has an overall height H and the ratio of H:D is less than 0.93.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.

Abstract: An aerofoil blade having a root portion provided with a low friction coating layer. The low friction coating layer is affixed to the root portion by an adhesive layer. The adhesive layer has a service temperature of 125° C. or more, for example 140° C. or more.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a convex leading end, a trailing end, and first and second sides that join the convex leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. An arced rib is disposed in the internal core cavity and arcs toward the convex leading end. The arced rib and the convex leading define there between an arced cavity. An arced baffle is disposed in the arced cavity.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

Abstract: A blade for a turbomachine, a tip for a blade of a turbomachine and a related method are disclosed. The blade may include a tip body having a shape at least partially configured for coupling to an airfoil body of the blade; at least one coolant passage in the tip body configured for fluid communication with at least one coolant passage in the airfoil body; and a retention member extending from the tip body for coupling to a tip retention member seat in the airfoil body. The tip can be replaced, allowing for changes in the coolant passages in the tip of a blade.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.

Abstract: Blade for a turbine, comprising a blade root and an airfoil (13) extending radially outwards from the blade root (12), the airfoil (13) comprising a first internal cooling circuit including an intrados cavity (33, 36) extending radially along the intrados wall (16) and a first inner wall (47, 45) arranged between the intrados wall (16) and the extrados wall (18), an extrados cavity (34, 37) extending radially along the extrados wall (18) and a second inner wall (47, 43) arranged between the intrados wall (16) and the extrados wall (18). The first cooling circuit includes one inner through cavity (35, 38) defined between two through walls (59, 57, 55, 53) each extending between the intrados wall (16) and the extrados wall (18). The intrados cavity (33, 36), the extrados cavity (34, 37) and the inner through cavity (35, 38) are fluidly connected in series.

Abstract: A structure for improving performance of cooling a blade of a gas turbine is provided in which interaction vortexes are generated between working fluid flowing along a surface of the blade and cooling fluid discharged onto the surface from an internal flow passage of the blade. The blade includes a surface structure formed by a gas hole having an outlet communicating with the surface of the blade to discharge the cooling fluid; and a vortex relief generator disposed so as to protrude from an inner periphery of the outlet and configured to generate counter vortexes having directionality opposite to the interaction vortexes so that the interaction vortexes are relieved by collision with the counter vortexes. The vortex relief generator includes a pair of opposing fins disposed in a path of the cooling fluid, each of which has a first surface to change a flow direction of the cooling fluid.

Abstract: A nozzle or blade for a turbomachine includes an airfoil body including at least one first coolant passage, and an edge opening in a leading edge or a trailing edge of the airfoil body. The edge opening has an edge coupon retention member seat in or on an inner surface of the airfoil body. An edge coupon has a shape at least partially configured for coupling to the edge opening in the airfoil body. The edge coupon includes an edge coupon body, at least one second coolant passage in the edge coupon body configured for fluid communication with the at least one first coolant passage in the airfoil body, and a retention member extending from the edge coupon body for coupling to the edge coupon retention member seat in the airfoil body.

Abstract: Techniques for forming a dual-walled component for a gas turbine engine that include chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures and bonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, with the plurality of support structures defining at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

Abstract: A turbine blade in an industrial gas turbine includes a blade surface to be cooled by a film of cooling fluid, a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion, and a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole, wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.

Abstract: An airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.

Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.

Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Abstract: A component for a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A skin core passage is defined immediately adjacent the first surface, and at least one pedestal interrupts a flow path through the skin core passage.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. First and second platforms are attached, respectively, with the first and second ends. A cooling passage circuit extends at least in the first platform and the airfoil section. The cooling passage circuit includes a first plenum in the first platform adjacent at least the first side of the airfoil wall, a hybrid skin core passage embedded in the first side of the airfoil wall and that extends longitudinally, and a resupply passage that connects the first plenum with the hybrid skin core passage.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes a seal ring body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a segmented spline that extends from the radially outer face of the seal ring body, the seal secured to the radially inner face of the seal ring body

Abstract: Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.

Abstract: A blade made of layered material, such as composite material, configured for exposure to a fluid flow, comprises skins (1, 2) defined between a leading edge (3) and a trailing edge (4) which skins in cross-section form a flow profile. The layered material may consist of several layers of fiber material (5, 5?, . . . ) impregnated with a matrix material, wherein layers of fiber material each comprise a respective body portion (6, 6?, . . . , 13) between and transverse to the skins and each at least a respective skin portion (7, 7?, . . . ; 8, 8?, . . . ) that forms part of the skins. The said skin portions all extend from the related body portion in the direction of the trailing edge. Of said skin portions at least two consecutive skin portions of the one skin overlap and/or two consecutive skin portions of the other skin overlap each other.

Abstract: A fixture for masking a gas turbine engine blade, the blade having a root, a platform and an airfoil, the platform having inner and outer surfaces and peripheral faces extending between the surfaces, the fixture including a base with a receptacle for receiving the root of the blade; a removable sidewall mountable to the base to form a masking box with the receptacle that shields the root; a first removable Z plane detail mountable to the base, the first removable Z plane detail providing a first electrical contact point to the root; and a second removable Z plane detail mountable to the removable sidewall, the second removable Z plane detail providing a second electrical contact point to the root

Abstract: A bladed disc comprising a disc hub 110; a set of blades 120 angularly distributed around the disc hub; wherein there is variation in a geometric parameter between the blades. The blades are positioned around the disc hub such that for a majority of pairs of neighbouring blades in the set, an interval between values of the geometric parameter between the blades of the pair is less than 0.5 standard deviations of the geometric parameter for the set of blades.

Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.

Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, a first shear tube may extend through the airfoil and relatively orthogonal to the first platform and the second platform, wherein the first shear tube extends through the first platform and the second platform. In various embodiments, a second shear tube may extend through the airfoil into the first platform and the second platform parallel the first shear tube.

Abstract: An impeller tube-type nozzle for a gas turbine, with an inlet section, a retraction section and an outlet section. The inlet section is a section of annular channel, the retraction section comprises multiple gas flow channels separated by multiple blades, each gas flow channel is encircled by an outer peripheral wall face, an inner peripheral wall face, a suction face of one of two adjacent blades and a pressure face of the other of the two adjacent blades, and inlets of the gas flow channels have a fan-shaped cross section. For each gas flow channel, along the direction of gas flow from the inlet of the gas flow channel to the outlet the fan-shaped cross section gradually smoothly transitions into a circular cross section.

Abstract: One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment.

Abstract: An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

Abstract: An example hybrid aircraft propulsion system includes one or more parallel propulsion units, each of the parallel propulsion units comprising: a first propulsor; a gas turbine engine configured to drive the first propulsor; and an electrical machine selectively configurable to: generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the first propulsor or the gas turbine engine; and drive the first propulsor using electrical energy received via the one or more electrical busses; and one or more series propulsion units, each of the series propulsion units comprising: a second propulsor; and an electrical machine selectively configurable to: generate, for output via the one or more electrical busses, electrical energy using mechanical energy derived from the second propulsor or the gas turbine engine; and drive the second propulsor using electrical energy received from one or more electrical busses.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A turbine shroud segment has a body extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. Upstream and downstream plenums are defined in the body. The upstream plenum has a plurality of cooling inlets. The downstream plenum has a plurality of cooling outlets. A flow constricting slot extends across the body between the first and second lateral edges. The flow constricting slot fluidly connects the downstream plenum to the upstream plenum.

Abstract: System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil. The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil. The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.

Abstract: A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

Abstract: A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

Abstract: The present application relates to an exhaust steam waste heat recovering and supplying system used for air-cooling units in large thermal power plants. Each of the two steam turbines has independent exhaust steam extraction system, and the exhaust steam extraction system of each steam turbine is connected with corresponding pre-condenser to heat the return water of the heating network. The exhaust steam extraction system of each steam turbine is further connected with the corresponding steam ejector; the exhaust port of each steam is connected with the corresponding steam ejector condenser to heat the return water of the heating network. The exhaust steam waste heat of the air-cooling units in a thermal power plant can be recycled in high efficiency to improve the utility rate of the exhaust steam, increase heating capacity, reduce cold end loss to the largest extent, and maximize the energy saving benefits.

Abstract: A Rankine cycle plant for the regasification of liquefied gas, includes: a Rankine closed loop system; a source of liquefied gas at a cryogenic temperature operatively coupled to a condenser to receive heat from a working fluid from an expansion turbine to take the liquefied gas to the gaseous state; a source of a heating fluid at a temperature higher than the cryogenic temperature operatively coupled to an evaporator to transfer heat to the working fluid coming from the condenser. The expansion turbine is radial centrifugal with at least one auxiliary outlet interposed between successive stages. The condenser is multilevel and has at least two condensing chambers, wherein a lower chamber being connected to an outflow opening of the expansion turbine and an upper chamber connected to the auxiliary outlet of the expansion turbine.

Abstract: A power plant and method for preserving a power plant, the power plant having a steam turbine with a shaft, further including a condenser mounted downstream of the steam turbine in the direction of flow of the steam, a vacuum pump mounted downstream of the condenser, a compressed steam system with shaft seals, and a compressed steam supply line extending into the shaft seals; a first nitrogen line extends into the condenser, and a second nitrogen line as well as a recirculation line that branches off the vacuum pump extend into the compressed steam supply line.

Abstract: A cooling system includes a first circuit (A) configured to cool a combustion engine (2) and a second circuit (B) configured to cool a condenser (19) in a WHR system. The second circuit (B) has a second radiator (16), a first inlet opening (B1i) at which the second circuit (B) receives a coolant from a first position of the first circuit (A), a condenser inlet line (18) configured to direct coolant to the condenser (19) and an outlet opening (Bo) at which the coolant is directed back to the first circuit (A). The second circuit (B) further has a second radiator bypass line (14) directing coolant past the second radiator (16), and a second valve device (13, 13?) configured to distribute the coolant between the second radiator (16) and the second radiator bypass line (14) such that a coolant mixture is received in the condenser inlet line (18) which is able to cool the working medium in the condenser (19) to a desired condensation temperature.

Abstract: Methods and systems are provided for a valve system for actuating two cylinder valves in an engine. In one example, the valve system may include a single pump and a solenoid valve capable of non-concurrently actuating the two cylinder valves coupled to separate cylinders.

Abstract: A connection unit connected to a rotation body by fitting to transmit a rotation force includes a rotation shaft, having a width across flat portion; and a core member, having fitting portions fitted to the rotation body in a direction perpendicular to the width across flat portion and an annular portion that the width across flat portion are slidably fitted, and held on the rotation shaft to be capable of moving relatively in two dimensions along the width across flat portion while rotating integrally with the rotation shaft. Accordingly, generation of vibration or noise can be prevented, and easiness of assembly work, cost reduction, miniaturization and the like can be achieved.

Abstract: A variable camshaft timing (VCT) assembly for controlling the angular position of concentric camshafts includes an independent VCT device that is configured to couple with a first concentric camshaft and change an angular position of the first concentric camshaft relative to an angular position of a crankshaft; and one or more dependent VCT devices mechanically linking an output of the independent VCT device with a second concentric camshaft, wherein the dependent VCT device(s) change(s) an angular position of the second concentric camshaft relative to the angular position of the first concentric camshaft based on angular movement of the output of the independent VCT device.

Abstract: An internal combustion engine includes a valve seat insert within an engine housing, and a gas exchange valve. The valve seat insert has a compound valve seat with a valve recession-resistive profile formed by a leading radius contacted by the valve seat at an early wear state of the valve head and valve seat insert, a trailing radius contacted by the valve head at a later wear state of the valve head and valve seat insert, and an outer seat face. The compound valve seat is shaped and proportioned to cushion contact by a gas exchange valve and retard valve recession.

Abstract: A valve seat insert for a gas exchange valve controlling gas exchange of a cylinder includes an insert body having an inner peripheral surface, an outer peripheral surface, and a valve seating surface structured to contact the gas exchange valve at a closed position and profiled to limit valve recession thereof. The valve seating surface includes an arrangement of linear segments and curved segments forming crowns to contact the gas exchange valve at different wear states.

Abstract: The invention relates to a process for manufacturing an internally cooled valve, said process involving providing an externally at least partly cylindrical semifinished product (2), creating or increasing the depth of an at least partly cylindrical cavity in the semifinished product (2) in a hot-working procedure using a male die such that a valve blank is formed; during the hot-working procedure, a recess on an end face of the male die forms a structure on the bottom of the cavity.

Abstract: A method for controlling an engine having a continuous variable valve duration (CVVD) apparatus is provided. The method includes: correcting a torque required by a driver; transmitting, by a hybrid control unit (HCU), a start signal to an engine control unit (ECU) when the corrected torque satisfies conditions required to drive the engine; determining a target CVVD value for operation of an intake CVVD apparatus corresponding to the corrected torque; determining a target current value corresponding to the target CVVD value; and changing the target CVVD value to a synchronizing CVVD value when a current state of the engine is in a cranking interval, wherein the synchronizing CVVD value is configured to synchronize starting revolutions per minute (RPM) of the engine with RPM of an automatic transmission or RPM of a motor generator.

Abstract: A valve drive for an internal combustion engine has a first camshaft which is rotatably mounted in a first and a second camshaft bearing and which includes at least one cam with a first cam curve and a second cam curve that differs from the first cam curve, wherein a gas exchange valve can be actuated by the first or the second cam curve. A camshaft section is provided, by which the cam can be moved by an actuator such that the gas exchange valve can be actuated either via the first or the second cam curve. The first camshaft and the cam have a fixed position relative to each other. The first camshaft can be axially moved in the first and the second camshaft bearing.

Abstract: A transfer for a four-wheel drive vehicle, the four-wheel drive vehicle configured to disconnect a propeller shaft from a power transmission path between an auxiliary drive wheels and a driving power source when the four-wheel drive vehicle travels by two-wheel drive, includes a second output rotating member and an oil pump. The second output rotating member is configured to output a driving power to the propeller shaft. The oil pump is configured to rotationally drive in conjunction with rotation of the second output rotating member via a first one-way clutch. The first one-way clutch is configured such that the oil pump supplies a lubrication oil to a wet clutch when the four-wheel drive vehicle travels forward by the four-wheel drive. The oil pump is configured to stop supplying the lubrication oil to the wet clutch when the four-wheel drive vehicle travels forward by the two-wheel drive.