Abstract: A bumper assembly for down-hole use in a well. In one embodiment, the bumper assembly includes a fish neck, a cage, and a progressive rate spring disposed there-between. When a plunger strikes the top of the fish neck, the progressive rate spring dampens the force delivered by the plunger, thereby prolonging the useful life of the plunger and/or the bumper assembly.

Abstract: Upper and lower pressure equalizers couple to a lower end of a motor of an electrical, submersible pump assembly. An intermediate connection having a liquid flow passage connects the pressure equalizers. A connection valve located in the liquid flow passage closes the liquid flow passage prior to connecting the pressure equalizers with each other, and opens the liquid flow passage after the connection between the pressure equalizers is made. A sensor lower equalizer wire extends from a sensor unit through the lower pressure equalizer to a lower electrical terminal at the upper end of the lower pressure equalizer. A sensor upper equalizer wire connects to the lower electrical terminal and extends through, the upper pressure equalizer to an upper electrical terminal at the upper end of the upper pressure equalizer. A sensor motor wire extends downward from the motor into engagement with the upper electrical terminal.

Abstract: A method of estimating a characteristic of a formation includes: disposing a radar imaging tool in a borehole; generating a high frequency radar signal by a radar transmitter, the high frequency radar signal having a frequency configured to limit penetration of the radar signal to a near-borehole region of the formation, the near-borehole region including a surface of the borehole and a region of the borehole proximate to the surface; detecting return signals reflected from the near-borehole region; generating an image of the near-borehole region based on the return signals; and estimating a characteristic of the formation based on the image.

Abstract: A method, system, and non-transitory computer-readable storage medium for estimating pose of a drill are disclosed. The method may include receiving a location signal from a locating device, receiving a first signal indicative of an angular rate of the drill, and receiving a second signal indicative of an acceleration of the drill. The method may further include determining an operation state of the drill. The method may further include determining the pose of the drill based on the received location signal, first signal, second signal, and the determined operation state of the drill.

Abstract: A method for detecting a downhole position in a wellbore comprises: providing a set of signal emitters, each signal emitter in the set attached to a different position in the wellbore and each signal emitter configured to emit a signal having a unique characteristic; and providing a measurement tool comprising a signal detector configured to detect the different signals and a rotation device configured to rotatably contact a wall of the wellbore. The measurement tool is moved through the wellbore and one or more positions of the measurement tool in the wellbore is determined by detecting one or more of the signals and identifying the position of one or more of the signal emitters by the unique characteristic of each detected signal, and by detecting the number of rotations in a ranging wheel of the rotation detector that contacts the wellbore.

Abstract: A method has been disclosed for determining a position of a water/cement boundary in an annular area between two concentric pipes in a hydrocarbon well. The method comprises the steps of running a well tool (10) into a central pipe of the well, where the well tool (10) comprises a tool housing (11), a pulse generator (14) and a signal recorder (16) provided within the housing (11); generating an electromagnetic pulse by means of the pulse generator, thereby providing physical vibrations in the central pipe of the well; recording reflected acoustic signals from the well by means of the signal recorder (16); repeating the generating and recording steps for different vertical positions of the pulse generator in the well; organizing the recorded signals in a two-dimensional representation; filtering the organized recorded signals in order to identify, in the two-dimensional representation, a hyperbola (B); and providing an apex of the hyperbola (B) as the determined position of the water/cement boundary.

Abstract: A method for regulating an electromagnetic (“EM”) telemetry signal sent from downhole to surface includes determining a value of a controlled parameter of the EM telemetry signal, comparing the value of the controlled parameter to a configuration value, and adjusting the value of the controlled parameter in a first direction towards the configuration value while monitoring a feedback parameter of the EM telemetry signal when the value of the controlled parameter and the configuration value differ. The controlled parameter is one of transmission voltage and transmission current, and the feedback parameter is the other of transmission voltage and transmission current.

Abstract: A measurement tool having one or more measurement cells disposed in a fluid flow path is provided. Measurements are made in each of the measurement cells and a fluid type is identified based on the outcome of the measurements. A numerical value is associated with each measurement cell based on the identified fluid type, and a total fractional volume of the identified fluids is determined using the associated numerical values. There may be a relatively large number of measurement cells distributed so as to substantially cover the cross-sectional area of the flow path, relatively few measurement cells distributed randomly in fixed locations in the flow path, or a single measurement cell moveably located in the flow path. The measurement cells measure a property such as resistivity, capacitance, dielectric constant, or electrical impedance. The total fractional volumes of the identified fluids may be determined using a statistic.

Abstract: A guide rail rope deflection inhibition mechanism and method for a parallel soft cable suspension system in ultradeep vertical shaft construction. The guide rail rope deflection inhibition mechanism comprises a T-shaped installation support base, a rotating frame, a hydraulic support rod, and a chuck. The T-shaped installation support base comprises a vertical support rod and a horizontal support rod. The hydraulic support rod comprises an upper hydraulic support rod and a lower hydraulic support rod. The rotating frame comprises an upper Y-shaped frame and a lower Y-shaped frame. The chuck comprises an upper chuck and a lower chuck. The guide rail rope deflection inhibition method treats two guide rail rope deflection inhibition mechanisms as one group, and arranges at least two groups along the vertical direction on the shaft wall.

Abstract: Included is an anti-friction washer system comprising two steel washers coated with a zinc coating that is at least 0.0002 inch thick, the two washers adhered to one another by an adhesive having a melting temperature of 300° F. or less. Also included is a mine roof bolt system comprising: a bolt having a bolt head; a bearing plate; and the above-described anti-friction washer system located between the bearing plate and the bolt head. Also included is a method of manufacturing an anti-friction washer system including providing two zinc-coated washers, depositing a melted thermoplastic adhesive in a plurality of locations circumferentially around one surface of one of the washers, placing the other washer on top of the adhesive, applying pressure to the washers, and cooling the bonded washers.

Abstract: A coarse crusher for use at both face ends of a face conveyor in an underground mine is disclosed. The coarse crusher may have a pan module with a strand segment for guiding an endless conveying means. The strand segment may be delimited by a first pan outer longitudinal side and a second pan outer longitudinal side which lies opposite the first pan outer longitudinal side. The first pan outer longitudinal side and the second pan outer longitudinal side may have a plurality of first pan fastening apparatuses. The coarse crusher may further have a base-frame module fastened releasably via the corresponding first pan fastening apparatuses to one of the first pan outer longitudinal side and the second pan outer longitudinal side. The coarse crusher may also have a support-arm module fastened releasably to the base-frame module.

Abstract: A stator for a progressive cavity pump or motor includes a stator housing having a longitudinal axis. In addition, the stator includes a stator insert of a material moulded within the housing. The stator housing includes an outer tube having an inner surface. The stator housing also includes a plurality of framework elements disposed on the inner surface of the outer tube. Further, the stator housing includes at least one recess in the inner surface of the outer tube. The conjunction of the framework elements and the at least one recess define a plurality of chambers receiving insert material therein whereby the insert material is mechanically fixed axially, radially and torsionally within the outer tube.

Abstract: A method for patching a damaged polymeric erosion coating (250) on a gas turbine engine component. The method comprises removing a portion of the coating around a damage site (200; 202; 204) and applying a pre-formed coating patch (220).

Abstract: A turbine engine rotor component has a Ti-based first member (66) circumscribing an axis (500) and has either a circumferential array of integrally formed airfoils (62) or a circumferential array of blade retention features. A TiB particulate reinforced second member (90) also circumscribes the axis.

Abstract: A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device.

Abstract: A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

Abstract: A turbomachine component with a stress relief cavity includes an airfoil and a platform. The airfoil has a trailing edge. The platform has a trailing edge region, a seal strip slot and a stress relief cavity. The trailing edge region supports at least a part of the trailing edge. The stress relief cavity extends inside the platform into the trailing edge region and is an extension of the seal strip slot.

Abstract: An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.

Abstract: A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket.

Abstract: A blade for a gas turbine engine includes an airfoil having a tip with a terminal end surface and multiple squealer pockets recessed into the terminal end surface.

Abstract: An airfoil structure for a gas turbine engine includes an airfoil which includes a leading edge and a trailing edge. A platform is located adjacent a first end of the airfoil and includes a core passage that extends through the platform, a mate-face for engaging an adjacent airfoil structure and a set of impingement cooling holes in communication with the core passage that extend through the mate-face adjacent the trialing edge of the airfoil.

Abstract: A turbine shroud for a turbine of a gas turbine engine is disclosed. The turbine shroud is configured to direct products of a combustion reaction in a combustor of the gas turbine engine toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.

Abstract: Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a plurality of pores and a top sealing layer filling the plurality of pores, the sealing layer selected from the group consisting of: chromium, cobalt, nickel, polyimide, polytetrafluoroethylene and polyester.

Abstract: A co-formed element includes a core structure which has a root portion and is formed from a high thermal conductivity ceramic matrix composite material, and a low thermal conductivity layer co-formed with the core structure and surrounding the root portion of the core structure.

Abstract: A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture.

Abstract: A blade (100) has an airfoil (106) having a leading edge (114), a trailing edge (116), a pressure side (118), and a suction side (120) and extending from an inboard end (110) to a tip (112). An attachment root (108) is at the inboard end. The blade comprises an aluminum alloy substrate (102) and a coating at the tip (130). The coating (130) comprises an anodic layer (160) atop the substrate and an aluminum oxide layer (162) atop the anodic layer.

Abstract: An article (50; 100) has a metallic substrate (22), a bondcoat (30) atop the substrate, and a thermal barrier coating (28; 27, 28) atop the bondcoat. The thermal barrier coating or a layer thereof comprises didymium oxide ore and zirconia.

Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

Abstract: A variable-pitch vane comprising: a plurality of propeller blades (2), each being of variable pitch according to a blade rotational axis (A1) and each having a root (201), a plurality of rotor connecting shafts (6), each shaft having a foot (602) and a head (601). the root (201) of each blade being mounted on the head (601) of a rotor connecting shaft via a pivot (8) in such a way as to allow each blade (2) to rotate according to the blade rotational axis (A1), in which each blade (2) has a blade pitch, such that the blade rotational axis (A-i) of same is inclined relative to a radial axis (A2) passing through the foot (602) of the corresponding shaft.

Abstract: A method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is re- moved to form the guide vane.

Abstract: An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the vane carrier structure. A spacer is inserted into the recess. A first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess. At least one of the pairs of mating surfaces is inclined at an angle with respect to a radial plane of the vane carrier structure. A retention device secures the spacer to the vane carrier structure.

Abstract: A compressor for a gas turbine engine includes a plurality of rotating wheel assemblies, a plurality of static vane assemblies, and a case extending around the rotating wheel assemblies and static vane assemblies. The static vane assemblies include an inner band, an outer band, and a plurality of vanes extending between the inner and outer bands.

Abstract: An off-cambered vane for a guide vane assembly in a gas turbine engine is described. The guide vane assembly may comprise a nominal vane having a tip portion, a mid-span portion, and a hub portion. The mid-span portion of the nominal vane may adopt a nominal geometry and the hub portion of the nominal vane may adopt a common geometry. The guide vane assembly may further comprise an off-cambered vane having a tip portion, a mid-span portion, and a hub portion. The mid-span portion of the off-cambered vane may deviate variably with respect to the nominal geometry and at least one of the hub portion and the tip portion may adopt the common geometry.

Abstract: An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.

Abstract: An axial flow rotating machine having: a rotor that is provided with a plurality of rotor blades; a stator provided with a plurality of stator blades; an axial flow rotating portion formed by the rotor and the stator; and a diffuser connected to the axial flow rotating portion on the downstream side of the axial flow rotating portion. The final blade portion inner-circumferential inner wall, which is a portion of the inner-circumferential inner wall of the axial flow rotating portion, is formed so that the diameter thereof at the trailing edge position of the final blade is smaller than the diameter at the leading edge position of the final blade. In addition, the diameter of all or a portion of the diffuser inner-circumferential inner wall decreases in a direction of a first side in the axial direction, the first side being the downstream side.

Abstract: A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.

Abstract: A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

Abstract: The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.

Abstract: A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

Abstract: A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.

Abstract: A method of working a brush seal assembly for a turbine engine is disclosed and includes the steps of removing an alignment tab from a used brush seal assembly, restoring at least one dimension of the alignment tab to a desired condition and attaching the restored alignment tab to a new brush seal assembly.

Abstract: A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.

Abstract: Stator vane assembly includes plurality of vanes arranged in circumferential array, radially proximal mounting portion, radially distal mounting portion, and first latching mechanism. Each of plurality of vanes extends radially between radially proximal mounting portion and radially distal mounting portion, with each of plurality of vanes being pivotally mounted between radially proximal mounting portion and radially distal mounting portion. Plurality of vanes is movable between first arrangement allowing gas to flow across vanes, and second arrangement blocking gas flow across vanes. Pivot axis of each of plurality of vanes is offset from the line of aerodynamic centre of pressure of vane towards trailing edge of vane, and first latching mechanism holds plurality of vanes in first arrangement. Upon receipt of signal, first latching mechanism releases plurality of vanes so that gas flow through vane assembly causes plurality of vanes to move from first arrangement to second arrangement.

Abstract: One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis. The assembly further includes an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis.

Abstract: A turbofan engine including a fan section including a plurality of fan blades rotatable about an axis, a compressor including a plurality of compressor blades, a turbine including a plurality of turbine blades and a geared architecture driven by the turbine for driving the fan section at a speed and direction different than the turbine is disclosed. A rub strip proximate at least one of the compressor blades, the turbine blades and the fan blades slows rotation when engaged. The rub strip generates a torque opposing rotation when in an engaged condition that is between 2 and 6 times a torque encountered in a non-engaged condition.

Abstract: A debris monitor sensor system according to one disclosed non-limiting embodiment of the present disclosure includes a first passage disposed substantially linearly along a flow path, the first passage includes a sensor passage section. A second passage splits from the first passage and is offset from the flow path. An oil debris monitor is in communication with the sensor passage section.

Abstract: An exhaust system of a gas turbine engine includes an exhaust duct, and a venturi drainage device that drains fluid collected in the exhaust duct. The venturi drainage device includes an inlet in fluid communication with the exhaust duct. The venturi drainage device operates in an entrain mode when a flight condition occurs during operating of the gas turbine engine and operates in a drain mode when the gas turbine engine is not operating to drain the fluid from the exhaust duct.

Abstract: High-temperature machine components, more particularly, articles capable of operating in high-temperature environments, including for example turbines of gas engines, may be formed of a high temperature ceramic matrix composite that includes a ceramic substrate including silicon; an environmental harrier coating system including a silicon containing bond coat; and a diffusion barrier layer of a carbide or a nitride between the substrate of the article and the silicon bond coat of the environmental barrier coating system. The diffusion harrier layer selectively prevents or reduces the diffusion of boron and impurities from the substrate to the bond coat of the environmental barrier coating system.