Abstract: An apparatus for estimating a first property in a borehole penetrating the earth is described. The apparatus includes a carrier configured to be conveyed through the borehole. The apparatus also includes a first sensor disposed at the carrier and configured to perform a first measurement of the first property, the first sensor having a first direction of sensitivity; a second sensor disposed at the carrier and configured to perform a second measurement of a second property, the second sensor having a second direction of sensitivity; and a processor configured to receive the first and second measurements and to correct the first measurement using the second measurement in order to estimate the first property.

Abstract: A degradation pick or holder shank for facilitating installation, retention and removal is disclosed. The shank may comprise an axially compressive portion that may contract radially when stretched axially and then expand again radially when released. An installation tool may be used to stretch the shank axially during insertion into a bore and then release the shank to retain it within the bore.

Abstract: A roller cutter arrangement for a cutting wheel of a tunnel boring machine, including an interchangeable cup, a bearing block which is supported in the interchangeable cup in such a way that it is displaceable along a displacement axis, and a cutting roller unit having at least one cutting roller, which is rotatably supported in the bearing block and which acts along a working axis. The working axis is angled with respect to the displacement axis, so that cutting rollers of the cutting roller units may be situated in close proximity to one another, in particular in the central area of the cutting wheel.

Abstract: Provided is an apparatus for generation of a rotary motion comprising: a) an engine configured to operate by air pressure to create a rotary motion; b) a first air tank in air communication with the engine; c) a second air tank in air communication with the engine; d) one or more one way valves that limit backflow of air to the engine; and e) one or more conduits to allow for air communication between components of the apparatus; wherein the first air tank supplies air to the engine through the one or more conduits, the air subsequently leaving the engine and entering the first and the second tank, wherein passage of air through the engine creates a rotary motion.

Abstract: A component of a gas turbine engine is provided including at least one cooling hole formed in the component. The cooling hole has an interior surface that defines a flow path for air configured to cool a portion of the component. A feature is arranged within at least a portion of the cooling hole. The feature is configured to generate non-linear movement of the air as it flows there through.

Abstract: A blade/vane for a turbomachine that has a blade/vane outer skin and a blade/vane internal structure is provided. The blade/vane internal structure has a plurality of elongated support elements that extend obliquely to the radial direction of the blade/vane at least in certain sections, wherein the support elements are connected to each other and/or to the blade/vane outer skin, and the areas between the support elements are configured as hollow spaces.

Abstract: A blade with an airfoil profile for a gas turbine includes at least two opposite walls enclosing the inner part of the blade which form cooling channels and method of cooling the blade with a reduced cooling fluid flow rate at a side towards the bottom part of the blade in comparison to the side at the top part, wherein the airfoil profile extends from a bottom to a top part of the blade and at least one direct cooling fluid inlet is arranged at the bottom part of the blade, where at least one set of ribs is respectively arranged on the two walls, extending from the respective wall into the inner part of the blade, forming cooling channels in-between ribs with a channel cross-section smaller at the side towards the bottom part of the blade compared to the side at the top part.

Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

Abstract: An article includes a substrate and a multi-layered ceramic barrier coating on a substrate. The coating includes, from the substrate outward, a first layer of a low-dopant ceramic material and a second layer high-dopant ceramic material. The first layer has a columnar microstructure and the second layer has a branched columnar microstructure.

Abstract: A method for coating a surface of a substrate is provided. The method includes providing a suspension or a precursor comprising feedstock material suspended in a liquid medium. Further, the method includes spraying the suspension or the precursor onto the surface at a spray angle less than about 75 degrees to a tangent of the surface.

Abstract: A gas turbine including a fan platform positioned between adjacent fan blades of a fan of the gas turbine engine is provided. The fan platform defines an outer surface that at least partially defines an inner flowpath boundary of the fan. Additionally, the fan platform includes at least two components attached to one another. At least one of the components of the fan platform defines an enclosed void. An insert is positioned within the enclosed void formed of a material defining a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the fan platform, while also reducing a weight of the fan platform and an amount of stress on the fan platform.

Abstract: A variable pitch fan for a gas turbine engine includes a fan blade defining a pitch axis and attached at a radially inner end to a trunnion mechanism. The variable pitch fan also includes a disk having a disk segment with the trunnion mechanism extending at least partially through the disk segment. A key is positioned at least partially in a key slot defined in a base of the trunnion mechanism, and further positioned adjacent to a support member of the disk segment. The key defines a first contact line between the key and the key slot and a second contact line between the key and the support member. The first and second contact lines respectively define a first contact reference line in a second contact reference line. The first and second contact reference lines define an angle with the pitch axis of the fan blade greater than zero degrees and less than ninety degrees.

Abstract: A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void. An insert is positioned within the enclosed void which is formed of a material having a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the component, while also reducing a weight of the component and an amount of stress on the component. The component may be a fan platform positioned between a plurality of fan blades, an outlet guide vane, or another component of the gas turbine engine.

Abstract: An intershaft seal assembly including first and second or forward and aft carbon face seal rings supported on an annular housing and having first and second seal faces facing in opposite directions. Forward and aft springs operably disposed between housing and carbon face seal rings for biasing or urging carbon face seal rings in opposite directions. Annular forward and aft carriers mounted on and supported by annular housing and supporting carbon face seal rings. Forward and aft springs operably disposed between housing and the forward and aft carriers respectively. The springs may be wave springs. Inner and outer secondary seals may include inner and outer O rings disposed in annular inner and outer grooves in annular inner and outer surfaces in housing respectively and in sealing engagement with the forward and aft carriers. Carriers may be integral with carbon face seal rings in monolithic combined seal and carrier elements.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Abstract: A gas turbine engine component is provided. The gas turbine engine component has an internal cooling passage having first endwall and a second endwall. A primary inlet aperture is in fluid communication with a coolant supply and the first end of the internal cooling passage. An elongated rib is inside the internal cooling passage and proximate the primary inlet aperture. The elongated rib is configured to direct at least a portion of the coolant from the primary inlet aperture against a proximate one of the first or second endwall and then substantially reverse direction to flow downstream toward a second end of the internal cooling passage. A blade outer air seal (“BOAS”) assembly and a BOAS segment thereof are also provided.

Abstract: A segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.

Abstract: In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer.

Abstract: A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

Abstract: A fluid machine with variable vanes includes: a case, a plurality of vanes arranged along a circumferential direction of the case; a transmission ring rotatably provided in the case and configured to rotate with respect to the case; a transmission member provided on the transmission ring; and a driving assembly detachably attached to the case and including: a driving shaft; and a connection member connected to the transmission member through a through hole of the case provided at a position corresponding to the transmission member and configured to rotate together with the driving shaft, wherein the connection member is disengageably engaged with the transmission member such that the driving assembly is disconnected from the case through the through hole.

Abstract: An arrangement to prevent thermocouple chafing with a guide tube within a rotor disc cavity during gas turbine operation is provided. The arrangement includes an interstage seal housing, a guide tube, and a thermocouple including a tip portion, an elongated portion, a head portion, and an antichafing strip. The guide tube is disposed in a radially extending bore of the interstage seal housing. The tip portion extends radially inward into the rotor disc cavity, the elongated portion is disposed at least partially within the guide tube, and the head portion is disposed radially outward of the casing. The tip portion includes a temperature sensing element which measures the temperature of the rotor disc cavity. The antichafing strip is disposed along the length of the elongated portion so that it is at least partially disposed within the guide tube. A method to prevent premature gas turbine shutdown due to thermocouople failure is also provided.

Abstract: A containment for a continuous flow machine, in particular for a gas turbine, is disclosed. The containment has at least one annular housing with at least one axial section of lesser radial wall thickness and at least one axial section adjacent thereto of greater wall thickness, where the housing is designed and constructed so that the section of greater wall thickness is at a distance in the axial direction of the continuous flow machine from a trailing edge of a guide vane lying downstream in the direction of flow of the continuous flow machine, and extends downstream in the direction of flow of the continuous flow machine over a leading edge of the next downstream guide vane.

Abstract: The invention proposes a de-icing splitter nose at the inlet of the low-pressure compressor of a double-flow turbine engine. The splitter nose comprises an annular separation surface with a circular leading edge, the surface being adapted to separate an upstream flow into a primary flow and a secondary flow. The nose further comprises an electric de-icing device with a heating element having a series of parallel, electric, heating strips. The strips are inserted between two strata of dielectric material and are able to prevent the formation of ice on the annular surface, as close as possible to the leading edge.

Abstract: A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band define a first set of cooling channels and a second set of cooling channels formed beneath a gas side surface of the corresponding inner band or outer band. The inner band or the outer band further define a coolant distribution plenum that is in fluid communication with the first and second sets of cooling channels. The coolant distribution plenum provides a stream of coolant to at least one of the first set of cooling channels and the second set of cooling channels.

Abstract: A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure and suction sides. Rib structures located in the central cavity define radial central channels extending across the chordal axis. Radial near wall passages are defined between the rib structures and each of the pressure and suction sides of the outer wall. The radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel. The flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis.

Abstract: An engine component assembly is provided for impingement cooling including discrete cooling features. An insert is located opposite and adjacent to a cooled surface of the engine component and includes a plurality of angled impingement air holes. A cooling fluid flow path is flowing on one side the cooled surface of the engine component and adjacent to the insert and passes through the angled cooling holes of the insert in order to cool the cooled surface of the engine component. Additionally, a plurality of discrete cooling features may be located along the cooled surface of the engine component opposite the plurality of cooling holes in the insert.

Abstract: The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channelling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.

Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator.

Abstract: Heating systems for a rotor in-situ in a turbomachine are provided. In contrast to conventional systems that merely heat from an external turbine casing, embodiments of the disclosure heat the rotor. In one embodiment, a heating system includes a heating element to heat a portion of an exterior surface of the rotor. In another embodiment, the heating system may include a heating element(s) at least partially positioned within the rotor, and the rotor including the heating system. Each embodiment may include a controller to control operation of the heating element(s).

Abstract: Heating systems for a rotor in-situ in a turbomachine are provided. In contrast to conventional systems that merely heat from an external turbine casing, embodiments of the disclosure heat the rotor. In one embodiment, a heating system includes a heating element to heat a portion of an exterior surface of the rotor. In another embodiment, the heating system may include a heating element(s) at least partially positioned within the rotor, and the rotor including the heating system. Each embodiment may include a controller to control operation of the heating element(s).

Abstract: Heating systems for a rotor in-situ in a turbomachine are provided. In contrast to conventional systems that merely heat from an external turbine casing, embodiments of the disclosure heat the rotor. In one embodiment, a heating system includes a heating element to heat a portion of an exterior surface of the rotor. In another embodiment, the heating system may include a heating element(s) at least partially positioned within the rotor, and the rotor including the heating system. Each embodiment may include a controller to control operation of the heating element(s).

Abstract: In one embodiment, an exhaust heat collecting system of collecting exhaust heat in a fluid treatment system. The fluid treatment system includes a fluid path to convey at least an operating fluid or a cooled fluid among first and second heat source fluids, the operating fluid and the cooled fluid. The fluid treatment system further includes a fluid treatment module including an expansion module, a power generator and a condenser for the operating fluid, or including a heat absorbing module and a heat releasing module for the cooled fluid. The exhaust heat collecting system includes a water path to heat water by using the condenser or the heat releasing module, and a heater to heat the water from the water path by using the first or second heat source fluid or the operating fluid to produce the water to be used as hot water or to produce steam.

Abstract: The invention relates to a method for operating a steam turbine, the steam turbine being accelerated to a nominal speed by a device, such as, for example, a gas turbine or a generator. The steam turbine is charged with steam only when the steam has certain steam parameters, until the steam has reached the certain steam parameters, where the steam turbine is accelerated to a rated speed by the device.

Abstract: A system includes a camshaft disposed along an axis from a drive end to a opposite end, and the camshaft includes a plurality of journals configured to support the camshaft and is spaced along the axis. The camshaft includes a plurality of cams spaced along the axis, and is disposed along the camshaft in sets, where each set is disposed between a respective pair of journals of the plurality of journals. The camshaft includes a plurality of mass portions, where each mass portion is disposed between a set of cams and a respective journal. The plurality of mass portions is disposed along the camshaft such that a center of mass of the plurality of mass portions is nearer to the drive end than to the opposite end, and the plurality of mass portions is configured to increase a natural frequency of the shaft.

Abstract: A system for variable actuation of an engine valve of an internal-combustion engine includes a master piston and a slave piston, driven by the master piston. A control valve controls a communication of a volume of a pressurized fluid with a lower pressure environment, which is connected to a fluid accumulator, and an electronic control unit controls the electrically operated control valve. A device for dampening pressure oscillations is connected to the volume of pressurized fluid and includes an additional volume adapted for receiving fluid from the volume of pressurized fluid only when, following upon oscillations of the pressure in the volume of pressurized fluid, the pressure exceeds a maximum threshold value, which is higher than a mean pressure value that is set up in the volume of pressurized fluid when the master piston drives the slave piston in normal operating conditions.

Abstract: A hydraulic camshaft adjuster of the vane cell type, including a rotor and a stator and including a cover having fastening holes extending all the way through for accommodating fasteners. Via the fasteners the cover is fastened at an end face to the stator. The cover has a locking hole, into which a locking pin accommodated in the rotor can be displaced in an axial direction in order to lock the rotor in relation to the stator.

Abstract: A camshaft adjusting device, wherein said camshaft adjusting device has a lubricant supply unit, wherein the lubricant supply unit has a filter device for filtering the lubricant, wherein the filter device has at least one lubricant inlet, at least one lubricant outlet and at least one filter path, wherein the lubricant inlet and the lubricant outlet are fluidically connected to each other by way of the filter path, and wherein an output shaft of the camshaft adjusting device has two wall sections, wherein the at least one filter path is configured in a filter volume between the two wall sections, and wherein the lubricant inlet is at a smaller distance from the axis of rotation than the lubricant outlet, and the filter path extends at least in sections in the radial direction with respect to the axis of rotation.

Abstract: A valve operating apparatus includes: a first intermediate arm and a first rocker arm that are interposed between a first cam unit and a first valve; a second intermediate arm and a second rocker arm that are interposed between a second cam unit and a second valve; and hydraulic lash adjusters that rockably support the rocker arms. The intermediate arms are rockably supported by a rocker shaft. In the axial direction of the rocker shaft, the distance between the first transmission part and a bearing nearest thereto is shorter than the distance between the first pressure receiving part and a bearing nearest thereto, and likewise, the distance between the second transmission part and a bearing nearest thereto is shorter than the distance between the second pressure receiving part and a bearing nearest thereto.

Abstract: The present disclosure provides an oil pump system for a vehicle to control an oil flow or a flow rate of oil according to characteristics of an oil flow rate consumed for each component. The oil pump system includes: a mechanical oil pump, an electrical oil pump. In particular, the mechanical oil pump supplies oil to a lubrication component, and the electrical oil pump supplies oil to a cooling component or a control component. The mechanical oil pump and the electrical oil pump are independently operated.

Abstract: The first opening part penetrates the first partition wall that separates the crank chamber and the oil sump chamber. The lubricating device of the engine includes an oil mist generation control part. The oil mist generation control part disperses gas injected from the crank chamber into the oil sump chamber through the first opening part when the crank chamber has a positive pressure or restricts the flow of oil with which the injected gas collides, thereby controlling an amount of oil mist generated in the oil sump chamber.

Abstract: Methods and systems are provided for regulating oil flow to advance and retard chambers of a variable cam timing (VCT) system and to a thrust bearing of a camshaft via an oil control valve. In one example, an oil control valve may be housed within a cam journal cap the cam journal cap comprising a thrust bearing for receiving and retaining a camshaft. The cam journal cap may include a vertical bore configured to house the control valve, where the vertical bore may include a first port for receiving oil from an oil pump, a second port for flowing oil to an advance chamber of a VCT system, a third port for flowing oil to a retard chamber of the VCT system, a fourth port, coupled to the thrust bearing for flowing oil thereto, and a drain port for flowing oil to an oil sump.

Abstract: The present invention teaches a method and apparatus to quickly and inexpensively implement advanced, bypass grade, fine, or additional filtration to engines and hydraulic systems using any filter media through a single conduit means. The present invention has the ability to make quick hydraulic connection to the engine or hydraulic system, where oil is super cleaned, without major modifications as is the paradigm by traditional bypass filtration systems and without removing any lubricant from the engine or system that the present invention is connected to, as is the paradigm of traditional bypass filtering systems.

Abstract: A replaceable fluid container arranged to be removably seated in a dock to supply fluid associated with an engine, the replaceable fluid container comprising a plurality of fluid reservoirs, wherein each reservoir comprises a fluid port arranged to provide fluidic communication between the reservoir and a corresponding fluid circulation system associated with the engine when the replaceable fluid container is seated in the dock.

Abstract: Methods for indicating whether a crankcase of an engine is breeched are provided. One example method comprises restricting a communication of the crankcase with atmosphere, acting to increase or decrease a crankcase pressure, and indicating whether the crankcase is breeched based on the crankcase pressure. Another example method comprises sensing a crankcase pressure component, and indicating whether the crankcase is breeched based on the crankcase pressure component, the crankcase communicating with atmosphere via a conduit, a restrictedness of the conduit responsive to one or more of a crankcase pressure and a signal from an electronic control unit of the motor vehicle. Still other examples provide more particular methods for indicating whether the crankcase is breeched, and example configurations that enable the various methods.

Abstract: An aftertreatment system comprises a reductant storage tank and a SCR system including a catalyst for reducing constituents of an exhaust gas. A reductant insertion assembly is fluidly coupled to the reductant storage tank and the SCR system. A controller is communicatively coupled to the reductant insertion assembly. The controller is configured to: determine an initial pressure of the reductant, determine a first pressure at which the reductant is to be delivered to the selective catalytic reduction system and adjust an operating parameter of the reductant insertion assembly. The adjustment of the operating parameter results in an at least selective delivery of the reductant at the first pressure to the SCR system.

Abstract: A system includes a first diesel engine operable to drive a first device, a first DEF tank associated with the first engine and operable to provide DEF to the first diesel engine during operation, a second diesel engine operable to drive a second device, and a second DEF tank associated with the second engine and operable to provide DEF to the second diesel engine during operation. An external DEF tank is arranged to contain a quantity of DEF that is coupled to the first DEF tank and the second DEF tank and operable to selectively deliver DEF from the external DEF tank to each of the first DEF tank and the second DEF tank.

Abstract: The present invention is based on the application of heating resistors by a temperature regulation circuit in certain points of the catalyzer so that this comes into operation in the least time possible, reducing most of the amount of low molecular stability or environmentally harmful substances. Likewise, little tumult are added to each monolith duct to raise exhaust gas turbulence and increase the contact between the reduction and oxidation agent, whether it be platinum, palladium and rhodium.