Abstract: A downhole monitoring system and method that includes a sensor system with a sensor array with a number of sensors and a hub. Data measured by the sensors is processed by the hub and wirelessly communicated to a smart node. The sensor system may be mounted in the annulus formed between a borehole wall and an exterior surface of a well casing. The sensors may be configured to monitor the formation for microseismic events generated during hydraulic fracturing. The fracture growth and propagation may be monitored using the data obtained by the sensors. The data may facilitate real time control of the hydraulic fracturing operation.

Abstract: A real-time silica monitoring system can include a plurality of off-site sensors positioned at geographic locations off-site from a hydraulic fracturing well site that detect and measure quantities of airborne silica particles, a plurality of on-site sensors positioned at geographic locations on a hydraulic fracturing well site that detect and measure quantities of air-borne silica particles, and one or more mobile sensors suitable to be carried by individual persons that detect and measure quantities of airborne silica particles. A monitoring system can include a computer system that can aggregate and store airborne silica measurements taken by one or more sensors and communicate data to a user.

Abstract: This disclosure describes a novel method for predicting continuous wellbore mechanical properties such as static elastic stiffness and failure strength, where the properties solutions are deterministic and based on mechanical theory. It has at least three immediate applications: (a) continuous plots of mechanical properties vs. depth, (b) conceptual testing of the effect of changing constituent volume fractions, (c) ternary plots.

Abstract: The present disclosure relates to a formation sampling method that includes disposing a downhole tool comprising a packer and an expandable probe within a wellbore. The method also includes performing pressure transient testing by setting the expandable packer and the probe to engage a wall of the wellbore and measuring a pressure response at the expandable packer and the probe while withdrawing formation fluid into the downhole tool through the expandable packer. The method further includes monitoring a contamination level of the formation fluid during the pressure transient testing, and performing formation sampling with the probe in response to determining that the monitored contamination level meets a predetermined threshold.

Abstract: According to one embodiment, an expander includes a piston provided reciprocatively in a first direction in a cylinder, a crankshaft, an XY-separation crank mechanism provided between the piston and the crankshaft, which converts a reciprocating motion of the piston and a rotary motion of the crankshaft into one another, a cylinder head including an intake port and an outlet port, a suction valve which opens/closes the intake port, a discharge valve which opens/closes the outlet port, an intake-side valve mechanism which opens/closes the suction valve and an outlet-side valve mechanism which opens/closes the discharge valve. At least one of the intake-side and outlet-side valve mechanisms includes an XY separation drive mechanism.

Abstract: The object of the present invention is to provide a fluid rotary machine in which dead spaces can be reduced as much as possible even if the machine is enlarged by arranging rotary valves directly behind cylinder chambers. The fluid rotary machine in which first and second double-headed pistons (7, 8) intersecting within a case body (1, 2) move linearly back and forth within cylinders (16) due to the hypocycloid principle along with rotation of shafts (4a, 4b) and in which intake and exhaust cycles are repeated in chambers (22), wherein cylinder heads (17) for closing the cylinder chambers (22) are each provided with rotary valves (19) which are rotated by drive transmission from the shafts (4a, 4b) and which are provided with intake holes and discharge holes (19b) alternately communicated with the cylinder chambers (22) via communication channels (20a, 20b), and the rotary valves (19) intersect longitudinal axis of the opposing pistons (7, 8) and are capable of rotating parallel with output axil lines.

Abstract: A rotor for a rotary cylinder includes a body having a tube and a plate which has the first end integrally formed to the tube, and the second end of the plate extends radially relative to the tube. The plate is a solid plate and has a curved outer periphery. A first recessed area is defined in each of the top and the bottom of the plate. A waist is formed to the plate and located between the first and second ends of the plate. A resilient coat is coated to the body and includes a Y-shaped seal portion along the curved outer periphery of the plate so as to be movably in contact with the inside of the cylinder.

Abstract: A vane pump is disclosed that includes a plurality of vanes and radial slots configured to provide a gap between the vane and the radial slot such that the vane has a different angular position relative to the direction of rotation in a radially extended position compared to an angular position in a radially-retracted position. The different angular positions provide different orientation of the arcuate surface of the vane tip portion with respect to the cam body inner surface, thus providing different fluid stop points on the vane tip portion arcuate surface.

Abstract: A device for converting the kinetic energy of molecules into useful work includes an actuator configured to move within a fluid or gas due to collisions with the molecules of the fluid or gas. The actuator has dimensions that subject it to the Brownian motion of the surrounding molecules. The actuator utilizes objects having multiple surfaces where the different surfaces result in differing coefficients of restitution. The Brownian motion of surrounding molecules produce molecular impacts with the surfaces. Each surface then experiences relative differences in transferred energy from the kinetic collisions. The sum effect of the collisions produces net velocity in a desired direction. The controlled motion can be utilized in a variety of manners to perform work, such as generating electricity or transporting materials.

Abstract: A system for repairing dovetail slots includes a slot adaptor having a body configured and disposed to nest between first and second side walls of a dovetail slot, and a tool holder configured to be coupled with the slot adaptor. The tool holder includes a tool guidance system configured and disposed to direct a tool into contact with one of the first and second side walls of the dovetail slot. A cutting tool is mounted in the tool holder. The cutting tool includes a tapered surface configured and disposed to form a tapered recess in the one of the first and second side walls of the dovetail slot.

Abstract: A number of variations may include a method that may include casting or providing a central core comprising titanium aluminide; and metal injection molding a shell comprising titanium aluminide around the central core to produce a rotor assembly.

Abstract: A turbine blade having labyrinth of internal channels for circulation of coolant, the novel labyrinth geometry includes; inlet arranged on axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section, the second section having reduced cross section compared to first section; a first passage intersecting first section and extending through the blade body towards tip of the blade, a proximal end of leading edge passage arranged to capture incoming air flow; a main blade passage intersecting a downstream duct portion, the downstream duct portion arranged in axial alignment with the upstream duct portion but separate from upstream duct portion; and a restrictor passage intersecting with the mid-blade passage and extending towards a mid-blade duct portion, the mid-blade duct portion in axial alignment with the upstream and downstream duct portions and in fluid communication with the upstream duct portion.

Abstract: A cooled turbine runner for a gas turbine, in particular an aircraft engine, with turbine blades that are radially arranged at the circumferential surface of a rotor disk, wherein respectively a turbine blade is inserted with a profiled blade root into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk. A cooling device with at least one cooling air supply channel is provided, which extends at least substantially axially and at least over a part of the axial length of the blade root, and which has at least one inlet with an inlet opening at an inflow side of the blade root, wherein the inlet is embodied with a projection. A middle axis of the inlet has, in a direction oriented towards the inlet opening and in the area of the inlet opening, an extension component in the rotational direction of the rotor disk.

Abstract: A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.

Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.

Abstract: A blade assembly of a power plant having a modular structure, wherein blade elements include at least one blade airfoil, and at least one footboard mounting part. Blade elements can each have at its one ending a configuration for an interchangeable connection among each other. The connection of the airfoil with respect to other elements can be based on a fixation in radially or quasi-radially extension relative gas turbine axis, wherein the assembling of the blade airfoil in connection with the footboard mounting part is based on a friction-locked bonding actuated by adherence interconnecting, or on use of a metallic and/or ceramic surface fixing blade elements to each other, or on closure configuration with a detachable, permanent or semi-permanent fixation.

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

Abstract: A turbine blade is provided. The turbine blade includes a suction side wall including a first tip edge, a pressure side wall opposite the suction side wall and including a second tip edge. A tip wall extends between the suction side wall and the pressure side wall. The tip wall is recessed from the first tip edge and the second tip edge to define a tip pocket having a suction side wall tip section and a pressure side wall tip section. At least one turbulator is formed in the tip pocket on at least one of the following: the tip wall, the suction side wall tip section, and the pressure side wall tip section. The at least one turbulator formed on the tip wall is selectively positioned.

Abstract: A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Abstract: The present disclosure is directed to a root assembly for a rotor blade of a wind turbine and methods of manufacturing same. The root assembly includes a blade root section having an inner sidewall surface and an outer sidewall surface separated by a radial gap, a plurality of root inserts spaced circumferentially within the radial gap, and a plurality of spacers configured between one or more of the root inserts. Further, each of the root inserts includes at least one bushing surrounded by a pre-cured or pre-consolidated composite material. In addition, the spacers are constructed of a pre-cured or pre-consolidated composite material.

Abstract: A blade or a vane for a gas turbine engine. The blade or vane comprising an aerofoil and a leading edge member attached to the aerofoil. The leading edge comprises an electrically conductive support member and a nano-coating formed on the support member.

Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided.

Abstract: Nozzles and nozzle assemblies for gas turbine engines are provided. A nozzle includes an airfoil having an exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, an outer band disposed radially outward of the airfoil, the outer band including a radially outwardly-facing end surface, and an inner band disposed radially inward of the airfoil, the inner band including a radially inwardly-facing end surface. The nozzle further includes a flange extending radially from one of the radially outwardly-facing end surface or the radially inwardly-facing end surface. The flange is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies stacked together and generally having an L-shape in a circumferential cross-sectional view.

Abstract: A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.

Abstract: A turbine housing has a cavity that defines a turbine axis, and has a volute. The volute comprises a volute passage spiralling radially inwards towards the cavity, a substantially annular throat positioned around the cavity between it and the volute passage, and a tongue terminating at a distal tongue tip. In a plane containing the turbine axis and the tongue tip, the throat defines a line of minimum clearance, the volute passage and tongue tip co-operatively define a preliminary inlet area, and the tongue tip defines a tongue tip lateral centerline. The line of minimum clearance and the preliminary inlet area co-operatively define a line of passage offset, which connects the centroid of the preliminary inlet area and a point half way along the line of minimum clearance. The line of passage offset is not perpendicular to the turbine axis, and the tongue tip lateral centerline and the line of passage offset define an angle therebetween of at least 60 degrees.

Abstract: A turbine shroud segment is metal injection molded (MIM) about a low melting point material insert. The low melting point material is dissolved using heat during the heat treatment cycle required for the MIM material, thereby leaving internal cooling passages in the MIM shroud segment without extra manufacturing operation.

Abstract: An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of circumferentially spaced-apart vanes extending radially across the flow passage. At least one of the struts is aligned in the circumferential direction with an associated one of the vanes and forms therewith an integrated strut-vane airfoil. The adjacent vanes on opposed sides of the integrated strut-vane airfoil have uneven axial chords relative to the other vanes.

Abstract: An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly further includes a radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly from the outwardly-facing end surface and formed integrally with the outer end component, the feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure, the feature selectively positioned orthogonally to a force imparted into the airfoil assembly.

Abstract: A gas turbine engine with an air cooled turbine part in which spent cooling air for the turbine part is discharged into the combustor instead of into the hot gas stream of the turbine in order to increase efficiency of the engine. Turbine rotor blades and stator vanes are cooled. The spent cooling air is passed into a diffuser located between the HPC outlet and the combustor inlet where the spent cooling air is discharged along the inner and outer endwalls of the diffuser in directions substantially parallel to the inner and outer diffuser endwalls and at a greater velocity in order to energize the diffuser endwall boundary layers so that they can sustain higher diffusion rates and levels.

Abstract: A turbine stator vane assembly comprises a plurality of circumferentially arranged struts and a plurality of circumferentially arranged stator vanes. Each stator vane has a leading edge, a trailing edge and a chord length. Each strut has a leading edge, a trailing edge, a chord length, a pressure surface and a suction surface. The chord length of the struts is greater than the chord length of the stator vanes. The stator vanes are arranged in groups between adjacent pairs of struts and each group of stator vanes comprises a plurality of stator vanes. The circumferential spacing between adjacent struts is substantially the same and each stator vane in a group of stator vanes has a different chord length to the other stator vanes in that group of stator vanes.

Abstract: A turbine, in particular a high-pressure turbine, for an aircraft engine, with a housing at which turbine guide vanes are circumferentially arranged, wherein the turbine guide vanes have at least one interior space through which cooling air flows during operation of the turbine. At least one turbine guide vane has a cooling air passage in the area of an inner wall with respect to the radial direction of the turbine, via which the interior space of the turbine guide vane can be supplied with cooling air.

Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.

Abstract: In a seal structure that seals a gap between a first structure and a second structure which faces the first structure in a radial direction and rotates relative to the first structure, one of the first structure and the second structure has a base surface and a step surface that protrudes toward the other side from the base surface, and the other is provided with: a first fin which extends toward the step surface and forms a first gap between the step surface; a second fin that, on the downstream side of the first fin, extends toward the base surface and forms a second gap between the base surface; and a protrusion part that is disposed between the first fin and the second fin and that divides a leak flow, into a first vortex along the first fin and a second vortex along the second fin.

Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.

Abstract: A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.

Abstract: A steam valve 10 of an embodiment includes: a valve element 32 of a steam control valve 30, the valve element 32 being provided to be movable in an up and down direction; a valve element 42 of a main stop valve 40, the valve element 42 being provided under the valve element 32 coaxially with the valve element 32 to be movable in the up and down direction; a valve seat 60 with which the valve element 32 and the valve element 42 come into and out of contact; and a guide tube 43 slidably supporting a valve rod 41 including the valve element 42, and having a flange portion 43a at a bottom side in a casing 20.

Abstract: A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.

Abstract: A turbine ventilation structure includes: an exhaust diffuser including inner and outer tubes to form an exhaust passage for exhaust gas; a strut extending across the exhaust diffuser from a housing to support a bearing inside the inner tube; a strut cover in the exhaust passage that covers the strut; and a connecting member disposed downstream of the strut cover and including a hollow portion to connect the housing and the inner tube. The housing includes a first intake port to introduce an air from outside. The strut cover has a discharge hole at a rear edge portion thereof. The turbine ventilation structure includes a first ventilation passage extending from the first intake port through the hollow portion, then extending from an inner end portion of the strut through between the strut and the strut cover, and the discharge hole, into the exhaust passage.

Abstract: An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters.

Abstract: A line arrangement for a motor vehicle, preferably for a waste heat utilization system of a motor vehicle. The line arrangement includes one or more lines for conducting a fluid medium and is distinguished, in particular, by the fact that at least one line comprises at least one textile hose or is configured as at least one textile hose, and the textile hose has a textile structure and an inner sheath.

Abstract: Methods and apparatus to optimize ramp rates in combined cycle power plants are disclosed herein. An example method disclosed herein includes predicting a first setpoint for a gas turbine in a combined cycle power plant over a prediction horizon and predicting a second setpoint for a steam generator over the prediction horizon. The example method includes identifying a first steam property of steam generated by the steam generator in the combined cycle power plant based on the second setpoint. The example method includes comparing the first steam property to a second steam property of steam associated with a steam turbine in the combined cycle power plant and dynamically adjusting at least one of the first setpoint or the second setpoint based on the comparison.

Abstract: There is provided a combined cycle power plant in which a high-pressure steam turbine and an intermediate-pressure steam turbine can operate in a state where amounts of thermal effect thereof are close to a limit value, and capable of reducing start-up time. A combined cycle power plant includes: an exhaust heat recovery boiler that includes a high-pressure superheater which superheats steam for a high-pressure steam turbine, and a reheater which reheats steam for an intermediate-pressure steam turbine; bypass pipes through which steam bypasses the high-pressure superheater and the reheater; bypass valves that regulate flow rates of steam which flows through the bypass pipes; and a bypass controller that controls the bypass valves such that a difference between thermal effect-amount margins of the turbines is decreased.

Abstract: A hollow rocker shaft including a central opening defined by a radially inner surface and a separator secured in the central opening of the rocker shaft is provided. A radially outer surface of the separator engages the radially inner surface of the rocker shaft via a press-fit. The separator divides the central opening of the rocker shaft into (1) a first chamber extending between a first chamber axial end and the separator, and (2) a second chamber extending between a second chamber axial end and the separator. The separator includes an orifice defined between the first chamber and the second chamber that provides fluid connection between the first chamber and the second chamber.

Abstract: A camshaft phaser includes a stator; a rotor defining an advance chamber and a retard chamber with the stator; a valve spool that is rotatable about an axis and defining a supply chamber and a vent chamber with the rotor; an actuator which rotates the valve spool to change the position of the rotor relative to the stator by 1) supplying oil from the supply chamber to the advance chamber and venting oil from the retard chamber to the vent chamber and 2) supplying oil from the supply chamber to the retard chamber and venting oil from the advance chamber to the vent chamber; and a check valve which is displaceable axially between an open position which allows oil to flow from the vent chamber to the supply chamber and a closed position which prevents oil from flowing from the supply chamber to the vent chamber.

Abstract: A continuous variable valve timing apparatus for an engine includes: a housing, a rotor installed to be rotatable relative to the housing and connected to a camshaft, a locking pin configured to restrict rotation of the rotor relative to the housing when pushed by an elastic force to move linearly and pass through a relatively rotating surface between the housing and the rotor, an elastic member installed to provide the elastic force, a valve bolt coupled to the camshaft through the housing and the rotor, wherein the valve bolt includes a release passage through which a release pressure provided through the camshaft is transferred to the locking pin via the rotor, and a valve means for selectively blocking or unblocking the release passage, and an actuator installed to actuate the valve means of the valve bolt according to an actuation displacement.

Abstract: An intermediate phase adjustment apparatus of intermediate phase continuous variable valve timing includes chambers and a diverter valve balancing oil pressure between the chambers. The chamber includes an advancing chamber and a retarding chamber formed between a rotor and a stator and supplied with oil through an oil channel. The diverter valve balances oil pressure between the chambers by sliding along an oil line through which the oil moves only in one direction between the chambers so that the oil selectively moves from a chamber having higher pressure to a chamber having lower pressure due to a pressure difference.

Abstract: A Continuous Variable Valve Timing (CVVT) apparatus for an engine may include a housing, a rotor disposed to be rotatable relative to the housing, a locking pin passing through a facing relatively rotating surface between the housing and the rotor by elastic force so as to restrict rotation of the rotor relative to the housing by linear movement, and an oil control valve disposed such that oil is supplied to an advance chamber and a delay chamber provided between the rotor and the housing, in which, when a control duty value applied to the oil control valve is “0”, the oil control valve is fixed in a state in which the oil is supplied to the advance chamber.

Abstract: An intermediate phase adjustment apparatus of a CVVT includes check valves provided to prevent backflow of oil when the oil moves from one chamber to another chamber in order to secure a parking position of a lock pin in a CVVT of which an advance chamber and a retard chamber are formed between a rotor and a stator, and an oil inlet portion formed at the stator to correspond to inlet portions of the check valves, wherein an oil inlet portion provided at one chamber is formed larger than an oil inlet portion provided at the other chamber by a predetermined size, and the open angles of the check valves for making oil to flow into a chamber are increased, thereby preventing an offset occurrence by a cam torque.

Abstract: Provided is a control valve capable of reducing the axial length of a device as much as possible, thereby improving its mountability. An electromagnetic selector valve is equipped with a valve body functioning as a cam bolt for connecting a vane rotor to one end of a camshaft, a sleeve fixed to an inner peripheral surface of the valve body, and a spool valve element axially slidably housed in the sleeve for switching between supply and discharge of working fluid to and from each of a phase-retard working chamber and a phase-advance working chamber. The valve body has a male screw part formed on an outer peripheral surface and screwed into a female screw part formed in a cam bolt hole. The position of formation of the male screw part and the position of the spool valve element are arranged to axially overlap with each other.

Abstract: Systems and methods for varying a rotational relationship between a cam shaft and a crank shaft on an internal combustion engine (i.e., cam phasing) are provided. In particular, systems and methods are provided that facilitates a rotary position of a first component to be accurately controlled with a mechanism causing a second component, which can be coupled to the cam shaft or crank shaft, to follow the rotary position of the first component.