Abstract: A system includes an annular wellhead housing and an indicator assembly. The annular wellhead housing includes a shoulder and a first passage extending radially through the wellhead housing from an exterior surface of the wellhead housing to an interior surface of the wellhead housing. The indicator assembly is configured to extend through the passage, wherein the indicator assembly, when actuated, is configured to indicate whether a hanger disposed within the wellhead housing has landed on the shoulder.

Abstract: Apparatus and methods to image pipes of a multi-pipe structure can be implemented in a variety of applications. The multi-pipe structure may be associated with a well site, such as a multi-casing structure for a production well. Individual pipes of the multi-pipe structure may be investigated in a multi-stage process using delta-like responses, where previous stages provide inputs to subsequent stages. The results of multi-stage processing can be used to image defects in the multi-pipe structure.

Abstract: The present invention provides a methodology and system for formation boundary detection ahead and around of a drilling bit. By setting symmetrical design of receivers/transmitters around a transmitter/receiver and the direction of the receivers/transmitters, the system can measure the signals reflected by a formation boundary ahead of and around the drilling bit. The measured signals can be used to determine formation boundary positions.

Abstract: Various implementations directed to a continuous survey using magnetic sensors are provided. In one implementation, a method may include acquiring continuous survey data during an outrun data acquisition using a survey tool disposed within a previously drilled section of a wellbore. The survey tool may have one or more magnetic sensors, and the survey tool may be configured to ascend within the previously drilled section of the wellbore during the outrun data acquisition. The method may further include transmitting the continuous survey data to a computing system, where the computing system may be configured to generate a continuous survey of the previously drilled section of the wellbore based on the continuous survey data.

Abstract: A detection system to detect an object in a blowout prevention system of a production system includes a sensor coupled to the blowout prevention system and configured to send an ultrasonic pulse toward the object. The sensor is further configured to receive a signal including the ultrasonic pulse and noise after the ultrasonic pulse interacts with the object. The detection system also includes a controller coupled to the sensor and configured to identify the ultrasonic pulse in the signal using a first cancellation signal at a first time and a second cancellation signal at a second time. The controller is further configured to determine that the first cancellation signal corresponds to the noise in the signal at the first time, and determine that the second cancellation signal corresponds to the noise in the signal at the second time. The controller is configured to determine a characteristic of the object based on the ultrasonic pulse.

Abstract: The use of degradable components has become a more common practice in subterranean operations for such applications as temporarily isolating zones or diverting flow. A major concern of operators in using degradable tools is the ability to ensure that the tool has completely degraded and is no longer blocking or obstructing flow. This issue can be resolved through the use of degradable components that include one or more chemical additives that are released upon the partial or full dissolution of the degradable component, and which can be used to facilitate in the dissolution of the degradable component. The degradable component can optionally include tracer elements that are released upon the partial or full dissolution of the degradable component, and which can be detected at the surface to ensure the desired degradation or removal of the degradable component as well as hydraulic access to that stage.

Abstract: A system for wirelessly monitoring well conditions includes a set of wireless transceivers placed along a drill string inside a well, each transceiver placed within at least half the maximum distance that each transceiver can transmit data, and a power generator attached to each transceiver that powers the respective transceiver, the power generator including a first material that is of one polarity and a second material that is fixed in position and is of opposite polarity of the first material, wherein the first material is propelled toward the second material based on the motion of the power generator so that the two materials have a maximized point of contact to generate maximum power. The wireless transceivers may communicate using any wireless communication technology, including but not limited to Wi-Fi, Wi-Fi Direct, and BLE.

Abstract: A method of determining the presence of hydrocarbon-filled natural fractures with sufficient lateral extension in a well in which stimulation by hydraulic fracturing is intended to be carried out. Following perforation of an interval, a fluid is pumped into the well and a pressure response trace is collected. The fluid is pumped at a rate which is lower than the pump rate for the intended frac job and the data collection rate is higher than the data collection rate for the intended frac job. Characteristic elements are identified in the pressure response trace whose value and combination indicate the presence or absence of hydrocarbon-filled natural fractures with sufficient lateral extension in the interval.

Abstract: In accordance with presently disclosed embodiments, systems and methods for generating a reservoir fluid flow simulation are disclosed. The method includes: obtaining prior reservoir fluid flow simulations generated for the reservoir and a plurality of associated input attributes used to generate the prior simulations; analyzing a variability of the input attributes among the prior reservoir fluid flow simulations; obtaining actual reservoir performance data and associated fluid flow attributes over time; analyzing a variability of the fluid flow attributes; and comparing the variability of the input attributes generated using the prior simulations to the corresponding fluid flow attributes from the actual reservoir performance data.

Abstract: Methods for determining the hardness and/or ductility of a material by compression of the material are provided as a first aspect of the invention. Typically, compression is performed on multiple sides of a geologic material sample in a contemporaneous manner. Devices and systems for performing such methods also are provided. These methods, devices, and systems can be combined with additional methods, devices, and systems of the invention that provide for the analysis of compounds contained in such samples, which can indicate the presence of valuable materials, such as petroleum-associated hydrocarbons. Alternatively, these additional methods, devices, and systems can also stand independently of the methods, devices, and systems for analyzing ductility and/or hardness of materials.

Abstract: A cutter assembly for an undercutting machine for cutting a rock workface and a method of assembling a cutter assembly is provided. The cutter assembly includes a shaft mountable on the machine with one end extending from the machine, and a cutter device arranged in connection to the extended end of the shaft. The cutter device is connected releasably and rotationally rigid to the shaft with a locking arrangement. The locking arrangement includes a first locking device arranged to transfer substantially axial loads, and a second locking device arranged to transfer substantially radial loads.

Abstract: An internal combustion engine is provided using parts that can be produced simply and inexpensively, in which internal combustion engine the fuel is burned optimally by adjustments of compression ratio and valve control times and thus the least possible harmful exhaust gases are emitted while maximum effective power is achieved. Furthermore, all liquid and gaseous fuels can be used.

Abstract: A fan is equipped with a boss, a first blade member, and a second blade member. The boss has: a first end and a second end in an axial direction; an inclined surface inclined, in a direction from the second end to the first end, toward an axial center extending in the axial direction; and an outer peripheral surface located between the inclined surface and the second end. The boss is rotatable about the axial center. The first blade member is connected to the outer peripheral surface of the boss. The second blade member is connected to at least one of the inclined surface or the outer peripheral surface located between the inclined surface and a connecting portion where the first blade member is connected to the outer peripheral surface.

Abstract: A turbine blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.

Abstract: Turn caps for airfoils of gas turbine engines having exterior side walls, an exterior top wall extending between the exterior side walls, a first turn cap divider extending from the exterior top wall and positioned between the exterior side walls and defining a first turning feature between the first turn cap divider and the exterior side walls, the first turning feature comprising a first suction-side turn passage and a first pressure-side turn passage wherein the first turn cap divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the turn cap, and a merging chamber is formed in the turn cap wherein fluid flows passing through the first suction side turn passage and the first pressure side turn passage are merged at the merging chamber.

Abstract: Provided are a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade. This turbine blade has a blade body having hollow shape, cavities provided inside the blade body, and a cooling passage that opens from the cavities to the rear end portion of the blade body. The cooling passage includes: a first passage provided on the third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage provided on the rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.

Abstract: An airfoil having one-sided pedestals is disclosed. The airfoil may define various cavities, such as an inflow feed cavity, an impingement cavity, and an outflow cavity. The various cavities may be connected by crossover sections such as an inflow crossover section and an outflow crossover section. Cooling air may be conducted into the inflow feed cavity, out of the inflow feed cavity through an inflow crossover section into an impingement cavity, and through an impingement cavity. The cooling air may be conducted out of the impingement cavity and into an outflow cavity through an outflow crossover section. Various cavities may include one-wall pedestals. One-wall pedestals may be structures extending from a wall of a cavity into the void of the cavity, whereupon cooling air may impinge, effectuating convective cooling.

Abstract: A gas turbine engine may have a blade receiver for holding a fan blade, wherein the blade receiver is rotatable about a radial axis of the gas turbine engine. The gas turbine engine may also include a variable pitch mechanism comprising an actuation arm. The gas turbine engine may also include a splined index ring disposed between the actuation arm of the variable pitch mechanism and the blade receiver. The splined index ring may include an outer spline and an inner spline.

Abstract: A compressor section for a gas turbine engine includes an upstream portion that includes at least one upstream rotor stage. A downstream portion includes at least one downstream rotor stage configured to rotate with the upstream rotor stage. A transition duct separates the upstream portion from the downstream portion.

Abstract: A turbine vane frame apparatus includes: an annular inner band disposed about a centerline axis and defining an inner flowpath surface; an annular outer band surrounding the inner band and defining an outer flowpath surface; and an array of axial-flow airfoil-shaped vanes disposed between the inner and outer flowpath surfaces, wherein the vanes have at least three different chord dimensions.

Abstract: The invention relates to an intermediate case for a twin spool turbomachine for an aircraft, comprising at least one lubricant passage and piece (88a) associated with at least one of its vanes (24), comprising a lubricant passage (98a) extending along a passage axis (134a) and opening up into the lubricant duct (55a). The passage axis (134a) and the orifice axis (140a) are also at a spacing from each other along a circumferential direction (91), and a connection piece (125a) through which a connection conduit (142a) passes is firstly partially housed in the vane root (34) so as to create a communication between the connection duct (142a) and the lubricant passage orifice (124a), and secondly is partially housed in an end-piece support device (108a) or in the lubricant passage end-piece (88a), such that the connection conduit (142a) communicates with the lubricant passage (98a) in the end-piece.

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

Abstract: Aspects of the disclosure are directed to a system associated with an engine having a central longitudinal axis, including a first shaft axially extending along the central longitudinal axis, a second shaft coaxial with the first shaft, a first air seal that seals between the first shaft and the second shaft at a first axial location, a second air seal that seals between the first shaft and the second shaft at a second axial location, a first oil seal that provides intershaft sealing between the first shaft and the second shaft at a third axial location, a second oil seal that provides intershaft sealing between the first shaft and the second shaft at a fourth axial location axially adjacent to the third axial location, and a high pressure compressor that provides pressurized air to a first radially exterior side of the first air seal and to a second radially exterior side the second air seal.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes an attachment feature and a body. The attachment feature and the body are constructed of ceramic matrix composite materials. In an illustrative embodiment, the ceramic matrix composite materials form a blade track segment.

Abstract: A non-contact seal assembly is provided. This assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. An aperture may extend partially axially into the first seal shoe from the first shoe end and laterally within the first seal shoe. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.

Abstract: The main object of the invention is a sealing ring element (6s) of a turbomachine, comprising a sealing portion (6p) with a first area (6p1) and a second area (6p2), with the inner surface (6i) of a first area (6p1) being at the same radial distance from the axis (X) of the turbomachine, characterised in that the sealing portion (6p) comprises an annular cavity (6c) which opens into an inner surface of the second area (6p2) and extends into the first area (6p1), the annular cavity (6c) defining an upstream lateral wall (6m) and/or a downstream lateral wall (6v) forming an angle (?) which is strictly between 0 and 90°.

Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.

Abstract: A valve device includes a main steam valve that is provided on a steam flow channel, a regulating valve that is provided on the steam flow channel to be connected to the main steam valve in series and that includes a first valve seat and a first valve body, an overload valve that is provided on a branch flow channel which connects a portion of the steam flow channel between the main steam valve and the regulating valve and a steam turbine to each other and that includes a second valve seat and a second valve body, and a driving unit that drives the first valve body and the second valve body as a common driving source of the first valve body and the second valve body such that the first valve body and the second valve body are interlocked with each other.

Abstract: Provided is a turbine having a turbine regulating unit, a turbine protection unit, at least one safety block, quick-closing valves and regulating valves, wherein the quick-closing valves and the regulating valves can be actuated by associated switching and setting drives, wherein the at least one safety block is a pneumatic safety block, and in that at least one switching drive for direct or indirect actuation of a quick-closing valve is a pneumatic switching drive. The embodiment also relates to a method for retrofitting an existing turbine having a turbine protection unit, a turbine regulating unit, a hydraulic safety clock, quick-closing valves and regulating valves, wherein the quick-closing valves can be actuated directly or indirectly by associated hydraulic switching drives.

Abstract: A system and method for determining leakage in a fluid supply line assembly are provided. The system includes a source of pressurized fluid, a pressurized fluid load, and a fluid supply line coupled to the source and the load. The leak detection system also includes a source isolation valve configured to control a flow of fluid into the fluid supply line from the source, a load isolation valve configured to control a flow of fluid from the fluid supply line to the pressurized fluid load, and a processor communicatively coupled to a memory device. The memory device includes instructions that when executed by the processor, cause the processor to close the load isolation valve and open the source isolation valve to supply pressurized fluid to the fluid supply line, and after a predetermined interval, determine a leakage of pressurized fluid from the fluid supply line.

Abstract: Blade feedback systems and methods for determining a blade angle position and rotational speed of a plurality of propeller blades of a variable pitch propeller assembly are provided. Exemplary blade feedback system includes features for determining an axial position of a beta tube. Based at least in part on the axial position of the beta tube, the blade angle of the plurality of propeller blades can be determined. Exemplary blade feedback system can also include features for determining the rotational speed of the beta tube such that the rotational speed of the propeller blades can be determined.

Abstract: A compressor water-wash advisory system generates compressor water-wash notifications or initiates on-line water-wash cycles for a gas turbine or turbofan jet engine based on monitored health parameters of the engine. A high-fidelity model of engine compressor performance defines nominal expected values of engine performance parameters, such as compressor efficiency and air flow, as a function of current operating conditions. A tracking filter component compares the modeled performance parameters with actual calculated performance parameters obtained from sensor data, and maintains a separate actual model of engine performance that modifies the nominal performance parameter values to match the calculated parameter values using parameter modifiers. A health index is derived as a function of the parameter modifiers, and a water-wash notification is generated when the health index is indicative of a significant loss of fuel efficiency due to dirt accumulation in the engine's compressor.

Abstract: A method for cleaning a jet engine includes introducing a cleaning medium having solid materials into the engine by way of at least one discharging device, wherein the cleaning medium exits from the discharging device at an exit speed of 80 m/s or less.

Abstract: A gas turbine engine includes a rotatable component and a non-rotatable component. A seal is carried on one of the rotatable component or the non-rotatable component to provide sealing there between. The seal includes a geopolymer seal element.

Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.

Abstract: An airfoil may include an airfoil body, a root and a platform disposed between the airfoil body and the root. The platform may have a first mating surface and a second mating surface. The platform may include a pocket defined by an inner diameter surface of the platform proximate the first mating surface. A channel may be defined in the platform with an outlet of the channel defined in the second mating surface.

Abstract: A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.

Abstract: A turbine casing may comprise a casing body and a first heat pipe disposed in the casing body. The first heat pipe may comprise a first working medium. The first heat pipe may include a first vaporization section and a first condensation section. The first vaporization section may be located forward the first condensation section. A second heat pipe may be disposed in the casing body and may comprise a second working medium different from the first working medium.

Abstract: A bearing damper assembly for a bearing compartment of a gas turbine engine includes a squirrel cage, a bearing support, an outer sleeve, and an inner sleeve. The bearing support is disposed radially outward from a portion of the squirrel cage. The outer sleeve extends axially from the bearing support. The inner sleeve is attached to the squirrel cage and is disposed radially inward from the outer sleeve. An outward surface of the inner sleeve has a first contoured portion having a first axially extending contour and an inner surface of the outer sleeve has a second contoured portion having a second axially extending contour. The outward surface of the inner sleeve and the inner surface of the outer sleeve define a gap extending between the first contoured portion and the second contoured portion. The gap forms a fluid damper.

Abstract: A gas turbine engine includes a bearing compartment that has an inlet. A supply line splits into a supply conduit and a reservoir conduit that are fluidly parallel to one another for a length. The reservoir conduit fluidly rejoins the supply conduit at a junction. The supply conduit is fluidly connected to the inlet, and the reservoir conduit includes a flow restrictor upstream from the junction. A main pump is fluidly connected to the supply line and is configured to supply a lubricant to the bearing compartment through the supply line and supply and reservoir conduits in an operating state. The main pump has a non-operating state in which the reservoir conduit is configured to slowly refill the supply conduit through the flow restrictor.

Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.

Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

Abstract: There is disclosed an auxiliary rotation device 28 for a gas turbine engine 10. The auxiliary rotation device 28 comprises: an electric machine 30 configured to be coupled to a rotor of the gas turbine engine 10; and a dedicated electrical storage device 32 coupled to the electric machine 30. During a period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a generator so as to charge the dedicated electrical storage device 32. Following the period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a motor by discharging the dedicated electrical storage device 32 so as to cause the rotor to rotate for a period of time to provide even cooling of the rotor around its circumference. There is also disclosed a method of cooling a rotor of a gas turbine engine 10 using an auxiliary rotation device 28.

Abstract: The invention relates to a power generator. The power generator comprises a vessel provided with a heat exchanging unit for alternatingly heating and cooling an organic based working fluid contained in the interior of the vessel during operation of the power generator. Further, the power generator comprises a mechanical unit associated with the vessel and provided with a reciprocating moving element that moves responsive to the heating and cooling process. The heat exchanging unit is arranged for heating the working fluid from below an evaporation temperature and for cooling the working fluid from above the evaporation temperature. Further, the power generator comprises a pressure transferring structure for transferring a pressure exerted by gas in the vessel towards the mechanical unit for driving the reciprocating moving element.

Abstract: The present invention provides a method of operating an engine (14) having one or more cylinders (16) each having a piston (18) within the cylinder (16) and each piston (18) having an expansion stroke and a return stroke and a top dead centre (TDC) position and a bottom dead centre position (BDC) and said engine (14) employing a working fluid (WF) and a heat exchange fluid (HEF), comprising the steps of: introducing the HEF during the return stroke of the engine; introducing the working fluid (WF) during the expansion stroke of the engine; causing the exhaust valve to be opened at or near bottom dead centre of the piston BDC; delivering the HEF to the cylinder (16) after the exhaust valve has been opened; and closing the exhaust valve before TDC, such as to allow the working fluid to be compressed by the piston within the cylinder. The invention also provides an engine (14) capable of being operated in accordance with the method.

Abstract: A system for recycling heat or energy of a working medium of a heat engine for producing mechanical work is described. The system may comprise a first heat exchanger (204) for transferring heat from a working medium output from an energy extraction device (202) to a heating agent to vaporise the heating agent; a second heat exchanger (240) for transferring further heat to the vaporised heating agent; a compressor (231) coupled to the second heat exchanger (240) arranged to compress the further-heated heating agent; and a third heat exchanger (211) for transferring heat from the compressed heating agent to the working medium. A heat pump is also described.

Abstract: Provided is a control device for an internal combustion engine equipped with a cam switching device including a cam groove provided on the outer peripheral surface of a camshaft and an electromagnetic solenoid type actuator capable of protruding, toward the camshaft, an engagement pin that is engageable with the cam groove. The control device is configured, in causing the cam switching device to perform a cam switching operation, to perform energization of the actuator such that the engagement pin is seated on a forward outer peripheral surface, and to more lower, when an electric current (coil current) flowing through the actuator as a result of the energization is greater, an average electric voltage per unit time applied to the actuator in protruding the engagement pin toward the cam groove from the forward outer peripheral surface.

Abstract: A phase adjustment mechanism is constructed as a differential deceleration mechanism where a ring gear is relatively rotated on a basis of a difference in the number of teeth between the ring gear and an inner gear by revolution of an eccentric axis with reference to a rotation axis by an electric actuator. A coupling member is provided including a first engagement portion engaging with a driving-side rotational member in a displaceable manner in a first direction serving as a radial direction and a second engagement portion engaging with the inner gear in a displaceable manner in a second direction orthogonal to the first direction.

Abstract: Disclosed is a procedure to minimize NOx during varying engine loads in a 4-stroke diesel engine including at least one cylinder with a cylinder head, first piston on a connecting rod, one actuator mounted on the cylinder head and one of the actuator operated second piston lockable via a hydraulic circuit in various positions in a combustion chamber. The second piston, at the latest during the current compression stroke is actuated by the actuator and locked in the combustion chamber, where it by the first piston introduced air is compressed in a predetermined compression ratio to meet an existing engine load wherein the free operated inlet valve is brought to close the inlet stroke at a piston position where the volume of the combustion air as introduced at the end of the compression stroke gives the predetermined compression ratio and that the injector injects the stated amount of fuel.