Abstract: In situ density and compressibility of a fluid sample are determined for a fluid sample collected downhole. The density and compressibility of the fluid sampled is determined by measuring a distance to a piston contained within the sample chamber using an external magnetic field sensor that senses a magnetic field emanating from a magnet provided on the piston internal to the sample chamber. The testing is performed quickly and at the surface in a noninvasive fashion (e.g., without opening the sample chamber).

Abstract: In situ density and compressibility of a fluid sample are determined for a fluid sample collected downhole. The density and compressibility of the fluid sampled is determined by measuring a distance to a piston contained within the sample chamber using an external magnetic field sensor that senses a magnetic field emanating from a magnet provided on the piston internal to the sample chamber. The testing is performed quickly and at the surface in a noninvasive fashion (e.g., without opening the sample chamber).

Abstract: Methods and devices for collecting fluid include a self-closing system that automatically halts fluid collection once a sufficient amount of fluid has been collected and a locking mechanism that automatically activates a pressure compensation system in order to maintain the collected fluid in the same phase in which it was collected.

Abstract: Methods and devices for determining a plus fraction of a plus fraction of a gas chromatogram are provided. A gas chromatogram may obtained, such as from a downhole gas chromatograph module of a fluid analysis tool. The plus fraction of the gas chromatogram may be determined using one or more of a ratiometric determination, fitting an exponential decay function, and fitting a probability density gamma function.

Abstract: The present invention relates to a ground milling machine, in particular a road milling machine, a recycler, a stabilizer or a surface miner, comprising a milling drum with a milling drum width (a) extending along its rotational axis and with at least two chiseling devices, each of which comprises a chisel and a chisel holder, and a sensor device for determining wear on the at least two chiseling devices in a contactless manner, said sensor device comprising a sensor for measuring a wear parameter of the at least two chiseling devices, the sensor being movable at least over a part of the milling drum width (a) in order to set an identical measurement angle (?) and an identical position of the sensor relative to the at least two chiseling devices in order to measure the wear parameter of the at least two chiseling devices. The present invention further relates to a method for determining wear on the at least two chiseling devices of the ground milling machine in a contactless manner.

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

Abstract: The invention relates to a yieldable rock anchor (10) comprising an anchor element (12) extending along a longitudinal center axis (A) and having a first end (14), a second end (16) and an outer surface (18). An anchor plate (20) is attached near the first end (14) of the anchor element, and an anchor head (22) is secured to the first end of the anchor element and adapted to clampingly engage the anchor plate (20). On its outer surface, the anchor element (12) is provided along at least substantially its entire length with a plurality of ribs (24). A plurality of sleeves (26), each sleeve having two opposing ends (28, 30), for covering some of the plurality of ribs is fixedly arranged on the outer surface of the anchor element (12) such that each of the opposing ends (28, 30) at least substantially sealingly engages the outer surface (18) of the anchor element (12).

Abstract: The invention provides a rock wail closure detection apparatus which includes an elongate member, variably extensible between a first wall and a second wall Of an underground excavation which comprises of a first and a second segment which are resiliently axially compressible relatively to one another when the waits close and an indicator module which produces a warning signal when actuated, attached to the first segment and an actuator attached to the second segment wherein on compression of the member, the actuator moves relatively to the module to actuate the module to produce the warning signal.

Abstract: Variable displacement systems, utilizing a phase relationship controller to determine and control the volumetric displacement of liquid and gas compression systems, including applications of said systems to continuously variable, constant speed power transmissions and to variable compression-ratio internal combustion engines.

Abstract: The present disclosure includes a system for balancing a turbine disk stack, including a high pressure turbine disk stack. A flange is grooved to accommodate and orient a slip ring. Balancing weights are attached to the slip ring to balance the turbine disk stack during rotation of a gas turbine engine.

Abstract: A wind turbine blade and an associated method of manufacture is described, wherein a structural bond line of the blade is positioned to be adjacent to a sandwich panel construction of the blade. By locating the structural bond line nest to a sandwich region of the blade, the buckling strength of the joint is improved and the risk of crack initiation in the adhesive joint is reduced considerably. This allows for a reduction in the amount of structural adhesive used in the blade, and/or a reduction in the amount of core material which is required in the sandwich panel to maintain the required blade stiffness. A particular advantage is provided in the region of the trailing edge of the blade, wherein the relocated structural joint considerably reduces the risk of buckling in the trailing edge side of the blade.

Abstract: Disclosed is a turbomachine including a stator, a rotor rotatable about an axis of rotation, and an annulus for carrying a core flow, the annulus having a side wall on the stator and a side wall on the rotor, at least one airfoil array having a plurality of airfoils being disposed in the annulus. In a departure from an ideal aerodynamic annulus contour, a radial annulus enlargement begins upstream of the airfoils and extends downstream up to an aft portion of the airfoil array that follows the ideal aerodynamic annulus contour. Also disclosed is an airfoil for such a turbomachine.

Abstract: A mixed flow turbine wheel (1) for a turbocharger includes a hub (6) extending axially between a nose (10) and a partial back wall (9) defining an axis of rotation in the axial direction. The partial back wall (9) extends circumferentially from the hub (6) to an outer peripheral edge (11). A plurality of turbine blades (7) are coupled to the hub (6) and extended beyond the peripheral edge (11). The blades (7) are spaced circumferentially about the hub (6) at equal intervals around the axis of rotation. At least one scallop cut (5) is formed in the peripheral edge (11) at the partial back wall (9) for balancing the turbine wheel (1) about the axis rotation.

Abstract: A turbomachine component includes a body defining an interior cooling channel in fluid communication with the exterior of the body for fluid communication with a cooling flow source. At least one flow modifying pedestal is disposed within the interior cooling channel extending in a first direction. The flow modifying pedestal includes at least one flow feature that extends from the pedestal in a second direction.

Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that includes a first wall and a second wall spaced apart and joined together at each of a leading edge and a trailing edge and extending between a root and a tip. An internal cooling circuit is disposed at least partially inside of the airfoil body. The internal cooling circuit has a first cooling passage disposed near a junction between the tip and the trailing edge and a fanned array of cooling holes that extend between the first cooling passage to at least the tip.

Abstract: A component, e.g. an aerofoil component like a turbine-blade or guide-vane, for a gas turbine engine, including first and second walls defining at least one passage for supply of cooling fluid to a portion of the component to be cooled, the portion including a slot via which cooling fluid passes from the passage to exit of slot for effecting cooling of the portion, wherein the slot includes at least one side wall, pair of opposite side walls, each having surface profile defining array of channels for passage of cooling fluid, and surface profile defining each of arrays of channels is undulating with the respective arrays of channels in two side walls being angled with respect to one another. The resulting internal cross-corrugated cooling arrangement promotes enhanced cooling of the trailing edge or other portion of the component by controlling flow rate of cooling air through slot and exhausted therefrom.

Abstract: A gas turbine engine component includes a wall having an inner surface and an outer surface. At least one non-rectangular slot extends through the outer wall surface and is in communication with a passage. The passages extend through the wall and include an inlet portion located at the inner surface and an outlet portion located at the outer surface. An intermediate portion fluidly connects the inlet portion and the outlet portion.

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract: A rotating blade for a gas turbine includes an airfoil extending in a longitudinal direction and having a leading edge and a trailing edge, whereby the airfoil is bordered at its outer end by a tip shroud, whereby the airfoil includes two or more internal passages, which run in longitudinal direction and are separated by solid webs, and whereby a plurality of shroud fins is arranged on top of the tip shroud to improve gas sealing against a corresponding stator heat shield. The stability and life time of the blade can be enhanced by selecting a position of each of the shroud fins to be exclusively above one of the webs and/or a leading edge wall.

Abstract: An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.

Abstract: A ceramic matrix composite blade may include an airfoil and a root. A protective metallic layer may be coupled to the root. The protective metallic layer may be plasma sprayed on the root. A portion of the protective metallic layer may be removed.

Abstract: An erosion resistant material has a continuous portion and discontinuous portions. The continuous portion has a continuous structure. The discontinuous portions are arranged inside the continuous portion to have a discontinuous structure. The discontinuous portions are formed of particles having an average particle diameter of 1 ?m or less. Further, the discontinuous portions are formed of a material having a surface hardness and a Young's modulus higher than those of the continuous portion.

Abstract: A device for dismantling a blade from a turbine, the turbine including a set of blades, the device including: a holding element including a blocking surface; a dismantling opening; an attachment system configured to attach the holding element to a shaft of the turbine, the attachment system producing a pivot connection between the holding element and the shaft of the turbine, the defining of an angular position of the holding element allowing a first function of dismantling at least one blade facing the dismantling opening to be carried out and allowing a second function of blocking a set of blades facing the blocking surface to be carried out.

Abstract: An attachment root of an airfoil is provided comprising a serration profile with a symmetry plane bisecting the serration profile. A first lobe of the serration profile has a first contact face angled 45 degrees from the symmetry plane. A second lobe of the serration profile has a second contact face angled 45 degrees from the symmetry plane. The first contact face may have a shorter length than the second contact face.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material. The component may further comprise an abrasive surface forming at least one surface of the body portion, and the abrasive surface may be configured to abrade an abradable material. The abrasive surface may be formed from electrical discharge machining of the metallic material.

Abstract: The invention relates to a turbine engine impeller, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes, characterised in that the integrated platform of each vane stops axially, upstream and downstream, to the right of the upstream and downstream transverse faces of the root, in that said tran

Abstract: To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.

Abstract: A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

Abstract: A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

Abstract: A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed.

Abstract: A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces. The first and second sealing rings slideably engage one another at a sliding wedge interface.

Abstract: Aspects of the disclosure are directed to a system for maintaining a seal about an engine centerline, comprising: a first component, a second component, and a dog-bone seal coupled to the first component and the second component, wherein the first component is configured with at least one spline that is configured to engage a slot in the dog-bone seal to radially center the dog-bone seal relative to the first component and the second component.

Abstract: A seal for a gas turbine engine may include a first cartridge, a second cartridge, and a wave spring. The wave spring may be located between the first cartridge and the second cartridge. The first cartridge may contact a first component to form a seal. The second cartridge may contact a second component to form a seal. The first cartridge may contact the second cartridge to form a seal. The wave spring may force the first cartridge to contact the first component, and the wave spring may force the second cartridge to contact the second component.

Abstract: It is an object of the present invention to provide a sealing mechanism that, while preventing a clearance that passes in an axial direction through an entire abutting surface without involving large resistance and that invites blow-by of a working fluid, can prevent adjacent seal segments from sticking to each other, and a method for manufacturing the sealing mechanism. A sealing device includes: an annular sealing ring that includes a plurality of seal segments annularly juxtaposed; a plurality of seal fins provided in an axial direction on an inner peripheral surface of the sealing ring; a joint surface on a circumferential end of the seal segment, the joint surface facing a joint surface on an adjacent seal segment; a groove that extends in a radial direction in the joint surface; and a protrusion formed by bending part of a surface that constitutes a long side of the groove toward an outside of the joint surface.

Abstract: A turbine engine impeller comprises a disc bearing vanes and an annular plate. The roots of the vanes are fitted in grooves and the root of each vane is connected to a blade by an integrated platform. The platforms of said vanes cooperate to form a radially inner wall of a duct for a flow passing through the blades. The annular plate comprises a transverse annular portion forming an axial stop of the roots of the vanes. The integrated platform of each vane has no spoiler and stops axially to the right of transverse faces of the root. The transverse annular portion of said annular plate bears, between the integrated platforms and the disc, an annular spoiler configured to extend in an axial space between the impeller and an adjacent module of the turbine engine so that said annular plate bears annular knife-edge seals of a labyrinth sealing joint.

Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.

Abstract: An engine includes circumferentially spaced turbine blades radially inward a casing and circumscribed by a carrier section having segments, each having a carrier wall radially inward the casing and radially outward the turbine blades. The wall has one or more portions facing the casing. At least one of the portions has one or more impingement apertures for air passage of a predetermined temperature from a feed source into impingement onto the casing. The segments are radially inward the casing and radially outward the turbine blades, with the portions of their respective walls facing the casing. A method of controlling the gas turbine engine turbine casing temperature includes: passing air of a predetermined temperature from a feed source through the apertures in the one or more portions and into impingement on the casing; and optionally exhausting the air impinged onto the casing from a space between the segment and the casing.

Abstract: A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g. during step climbs, results in better matching of radial expansion of the casing relative to the turbine blades, thereby enabling improved blade tip clearance control.

Abstract: A mobile low-flow water power generation system comprising at least one inlet hose, at least one power generator with an impeller configured for a flow rate of water from the inlet hose designed to generate an electrically compatible output voltage to a load, and an exit hose connected to the generator configured to pass water from the inlet hose without any back pressure.

Abstract: A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor.

Abstract: A valve for a turbomachine, has a valve cone and a valve seat, the valve cone being configured such that it can be moved in a valve body with respect to the valve seat. The opening and closing of the valve being achieved by the use of process-internal media taking into account different geometries of the working chambers and the use of thermodynamically different state variables.

Abstract: A device for automatic control of an angular position of turbine blades of a propeller device, in which the turbine blades are rotatable about a rotational axis and are pivotally displaceable about their respective pivot axes. The device comprises a set of control blades kinematically connected with the turbine blades, said control blades are pivotally displaceable about respective pivot axes once the propeller device is exposed to a flow of fluid. The device further comprises a transmission unit configured for transmitting pivotal displacement of the control blades to the turbine blades such that the turbine blades could be pivoted by the control blades. Pivoting of the turbine blades takes place simultaneously with the pivoting of the control blades. The angular disposition of the turbine blades is automatically set and remains invariant irrespective of direction of the flow of fluid.

Abstract: A borescope plug assembly includes a borescope plug having a shaft section and a tip section, a bushing engageable with the shaft section and a seal engageable with the tip section.

Abstract: An apparatus and system for mechanically connecting components are provided. The apparatus includes a mechanical connecting joint that includes a first joint member formed of a material having a first coefficient of thermal expansion (CTE) value, the first joint member comprising a first sidewall, a second opposite sidewall, and a body extending therebetween. The mechanical connecting joint further includes a second joint member formed of a material having a second CTE value, the second CTE being less than the first CTE. The second joint member includes a first leg facing the first sidewall, a second leg facing the second sidewall, and a connecting member extending between the first leg and the second leg. A first gap is formed between the first joint member and the first leg and a second gap is formed between the first joint member and the second leg.

Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

Abstract: A turbine component surface treatment process includes passing a UV-curable maskant through one or more fluid flow passages, wherein at least a portion of the UV-curable maskant exits the one or more fluid flow passages at an exterior surface of the turbine component, applying a UV light to the exterior surface of the turbine component, wherein the UV light cures at least a portion of the UV-curable maskant exiting the one or more fluid flow passages, and, treating the exterior surface with a treatment material, wherein the portion of the UV-curable maskant cured by the UV light substantially blocks the treatment material from entering the one or more fluid flow passages.

Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.