Abstract: A system for use in carrying out downhole coiled tubing applications with two-way telemetry over a single fiber optic thread. The system includes uphole and downhole assemblies each having unique couplers. Specifically, the couplers may be configured to secure the single fiber optic thread at one end thereof while having dedicated fiber optic channels at another side thereof for interfacing a fiber optic transmitter and receiver. Thus, fiber optic data may travel from a surface assembly over the thread for detection at the downhole assembly simultaneous with fiber optic data travelling from the downhole assembly to the surface assembly over the same thread.

Abstract: An illustrative method that includes positioning an acoustic transducer downhole substantially parallel to a borehole wall, thereby creating a fluid layer between the wall and the acoustic transducer, and measuring an acoustic impedance at the surface of the acoustic transducer at a resonance frequency of the fluid layer, thereby determining an acoustic impedance of the formation.

Abstract: A method, in some embodiments, comprises lowering a neutron wireline tool into a cased borehole containing casing fluid, determining a ratio of inelastic count rate to capture count rate using gammas passing through the casing fluid, and calculating a capture cross section of the casing fluid using the ratio.

Abstract: A mining machine includes a frame, a boom supported for pivoting movement relative to the frame, and a cutter head pivotably coupled to the boom. The cutter head includes a housing, a cutter shaft coupled to the housing, a cutting disc, and an excitation mechanism. A second portion of the cutter shaft extends parallel to a cutter axis. The cutting disc is coupled to the second portion of the cutter shaft and is supported for free rotation relative to the cutter shaft about the cutter axis. The cutting disc includes a plurality of cutting bits defining a cutting edge. The excitation mechanism includes an exciter shaft and a mass eccentrically coupled to the cutter shaft. The excitation mechanism is coupled to the first portion of the cutter shaft. Rotation of the exciter shaft induces oscillating movement of the second portion of the cutter shaft and the cutting disc.

Abstract: A high-frequency vibrating transverse drum cutter head, and a drum cutter machine and a tunnel boring machine with such drum cutter head are disclosed.

Abstract: A spring suspension clip configured to suspend a threaded rod member comprises a helical body with an upper end and a lower end, and a clipping section defined as the helical body. Then the clipping section is configured to conform to a threaded section of the threaded rod member to flexibly suspend the by two outward extensions into a space which is drilled and positioned within a section of rock which is to be grouted.

Abstract: The invention provides an end anchored rock bolt 20 which includes an elongate cylindrical body 12 which longitudinally extends between a proximal end and a distal end and a plug 18 at the distal end, which plug is diametrically larger than the cylindrical body 12, is at least partially tapered, tapering towards the proximal end, and is integrally formed on the body 12.

Abstract: A rotary piston and cylinder device (1) comprising a rotor (2), a stator and a shutter disc (3), the rotor comprising a piston (5) which extends from the rotor into the cylinder space, the rotor and the stator together defining the cylinder space, the shutter disc passing through the cylinder space and forming a partition therein, and the disc comprising a slot (3a) which allows passage of the piston therethrough, the slot provided between two surface portions which receive the piston therethrough,at least one of the surfaces defines a close-running region with the piston to provide a fluid seal, and for at least part of the period during which the piston passes through the slot, the close-running region is offset from a mid-plane which extends through the disc and is co-planar with the disc.

Abstract: A rotary piston and cylinder device (1) comprising a rotor (2), a stator and a shutter disc (3), the rotor comprising a piston which extends from the rotor into the cylinder space, the rotor and the stator together defining the cylinder space, the shutter disc passing through the cylinder space and forming a partition therein, and the disc comprising a slot (3a) which allows passage of the piston therethrough, the shutter disc comprising a circumferential surface (30) arranged to form a seal with a surface of the rotor, the circumferential surface defining a profile which forms at least one close running line (13b) with said rotor surface, and the at least one close-running line offset from a rotor plane (13) which lies on a radius of the rotor and which includes the axis of rotation of the rotor.

Abstract: A rotary piston and cylinder device (1) comprising a rotor (2), a stator and a shutter disc (3), the rotor comprising a piston (5) which extends from the rotor into the cylinder space, the rotor and the stator together defining the cylinder space, the shutter disc passing through the cylinder space and forming a partition therein, and the disc comprising a slot (32a) which allows passage of the piston therethrough, and a surface of the rotor and a surface of the stator opposing each other forming a close-running surface pair, and at least one of the surfaces comprising an abradable coating (10) which is provided with a plurality of recess formations, and the recess formations are discontinuous from each other.

Abstract: A shell-integrated fixed scroll includes a cylindrical shell that is integrated with an end plate on which a scroll wrap is erected, and has a proximal end entirely connected with an outer periphery of the end plate and a leading end extending in the axial direction. The wall of the shell partially forms a thick portion having a large thickness from a proximal-end-side end (first) surface to a leading-end-side end (second) surface. In the thick portion, a screw hole for a bolt for fastening a rear housing to the first surface extends from the first surface toward the second surface. A screw hole for a bolt for fastening a front housing to the second surface extends from the second surface toward the first surface. The thick portion is partially cut away in the circumferential direction between the two surfaces to form opposing surfaces facing each other in the axial direction.

Abstract: A blade assembly including a rotor; a body portion connected to the rotor and having a space therein; and at least one vibration reduction member provided in the space.

Abstract: According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.

Abstract: A turbine aerofoil having a leading edge, a trailing edge, an exterior surface including a suction side and a pressure side, at least an internal cavity for forming a cooling circuit having cooling slots between the suction side and the pressure side. The aerofoil includes a first trailing portion along the trailing edge where both the suction side and the pressure side extend from the leading edge up to the trailing edge in order that the first cooling slot is formed at the trailing edge, and at least a second trailing portion where the suction side extends from the leading edge up to the trailing edge and the pressure side extends from the leading edge up to a cut-back edge distanced from the trailing edge, in order that at least a second cooling slot is provided at the cut-back edge.

Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.

Abstract: An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.

Abstract: An airfoil of a gas turbine engine is provided including a leading edge extending in a radial direction, a tip extending in an axial direction from the leading edge, a first rib extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity within the airfoil, a second rib, the second rib and the first rib defining a serpentine cavity therein, a third rib extending axially within the tip, a flag tip cavity defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.

Abstract: A wheel disk assembly having a wheel disk, a plurality of blade devices, which are arranged thereon in a manner distributed over the circumference, and a plurality of sealing plates, which are retained in two annular grooves spaced apart from each other radially. In this assembly, the first annular groove is provided in the wheel disk and is bounded axially outward by an annular projection. The projection, in turn, is interrupted by a recess extending in the circumferential direction, with the result that a sealing plate can be inserted axially through the recess between the annular grooves. A closure piece is furthermore provided for closing the recess, which closure piece is captively retained on the sealing plate by a form fit.

Abstract: An integrally bladed disk is provided. The integrally bladed disk includes a rotor disk having a rim with a rim face and a flow path surface perpendicular to the rim face and integrally formed airfoils circumferentially spaced and extending radially outward from the rim, the flow path surface between adjacent integrally formed airfoils, each integrally formed airfoil having an airfoil edge. The rim face includes at least one first surface and at least one second surface formed in the rim face, the at least one first surface being substantially planar and axially proximal to the airfoil edge and the at least one second surface extending an axial depth into the rim face relative to the first surface.

Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.

Abstract: Stator vane for a turbine engine and including at least one portion made from material suitable for superelasticity. The portion made from material suitable for superelasticity is arranged so as to start to resonate at a predetermined speed of the turbine engine, in particular during a speed of the turbine engine typical of the cruising phase of the aircraft.

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: An assembly is provided for rotational equipment with an axial centerline. This assembly includes a primary seal device, a ring structure and a secondary seal device. The primary seal device is configured as a hydrostatic non-contact seal device. The primary seal device includes a plurality of seal shoes and a seal base. The seal shoes are arranged circumferentially about the axial centerline in an annular array. The seal base circumscribes the annular array of the seal shoes. The ring structure is axially engaged with the seal base. The secondary seal device is mounted with the ring structure. The secondary seal device includes a seal ring body and an alignment tab. The seal ring body is configured to substantially seal an annular gap between the ring structure and the seal base. The alignment tab projects out from the seal ring body and into an aperture in the ring structure. The alignment tab is adapted to substantially rotationally locate and/or fix the secondary seal device to the ring structure.

Abstract: An assembled ring shroud is provided. The assembled ring shroud may comprise a cover, a first ring layer, a key layer, and a second ring layer. The cover may operatively wrap around, contain, and secure the first ring layer, the key layer, and the second ring layer. The key layer may comprise a key that may act for position and anti-rotation. The key layer may comprise spacers to hold the keys in place. The first ring layer and the second ring layer may be configured to provide further strength and support to the assembled ring shroud.

Abstract: A blade outer air seal includes a seal arc segment that has a surface layer and an array of internal pockets. The surface layer defines a radially inner side of the seal arc segment. The surface layers conformal with the array of internal pockets such that the surface layer includes an array of ridges that correspond in location and shape to the array of internal pockets.

Abstract: A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. In use, a vortex is created in the cavity.

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 turbine shroud for an axial turbine, the shroud including: an annular array of arch shaped shroud segments each configured to be mounted to an inner surface of a turbine casing, the segment having an arched seal surface aligned with tips of a last row of turbine buckets in the turbine, and vanes positioned on an inner surface of each of the shroud segments and downstream in a direction of gas flow through the last row, the vanes extending inward from the inner surface towards an axis of the turbine.

Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.

Abstract: A control device 14 of a gas turbine that compresses a suctioned air with a compressor to obtain compressed air, mixes a fuel supplied from a combustor with the compressed air to burn the fuel and the compressed air to obtain a combustion gas, operates a turbine with the generated combustion gas to rotate a rotor, and discharges the combustion gas that has operated the turbine as a flue gas, the compressor including an inlet guide vane capable of adjusting the degree of opening and provided on an air-suction side, and temperature adjustment control to control the degree of opening of an inlet guide vane being executed along a temperature adjustment line indicating an upper limit temperature of a flue gas temperature defined according to a load of the gas turbine.

Abstract: A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.

Abstract: A blade monitoring system and method for a turbine assembly comprising rotating blades (14), the system comprising at least one sensor (10, 12) for transmitting a signal towards said rotating blades and detecting a time-varying return signal therefrom, and one or more processors (20) configured to calculate the time derivative of said return signal, generate a phase variation signal for said time derivative, determine minima points within said phase variation signal and measure said signal at said minima points so as to identify data representative of respective minimum path lengths, each said minimum path length corresponding to the returned signal as each respective blade passes said sensor, and generate, using said minimum path lengths, a time series of data representing the returned signal from individual blades as they pass the sensor.

Abstract: System for maintaining a turbine engine comprising said turbine engine of an aircraft comprising: an oil reservoir, a sensor able to measure an oil level in the oil reservoir, a transmission device, such as electrical wires, wireless transmitter circuit, etc., for transmitting a signal coupled to said sensor in order to transmit information relating to an oil level measured by said sensor, communication means, such as a display or a near field communications circuit coupled to said transmission devices, for communicating to the outside of the aircraft information representing an oil level measured by said sensor. The maintenance system further comprises a mobile apparatus able to communicate with said communication means and comprising a display for displaying said information representing an oil level to an operator situated on the ground outside the aircraft.

Abstract: The invention relates to an overspeed protection device of an aircraft engine

Abstract: A piping system of a steam turbine plant includes: a piping member including a first pipe section including a first passage, a second pipe section including a second passage, a connection section arranged between the first pipe section and the second pipe section and including a connection passage that connects the first passage and the second passage, and a third pipe section including a third passage connected with the connection passage through an opening, the first pipe section being supplied with steam; a steam stop valve connected with the third pipe section; and a turbine bypass valve connected with the second pipe section. An angle made by a first central axis and a second central axis is larger than an angle made by the first central axis and a third central axis.

Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.

Abstract: A vane adapted for use in a gas turbine engine is disclosed. The vane includes a forward following serpentine cooling path having a plurality of divider walls to direct cooling airflow. The serpentine cooling path optionally includes one or more bifurcating walls in the cooling path to split the airflow. The serpentine cooling path is in communication with an aft inlet in the vane and air passing through the serpentine cooling path exits a forward outlet in the vane into a forward rotor/stator cavity.

Abstract: Systems and methods for cooling a bearing may comprise a bearing ring, a rotational member coupled to the bearing ring, a bearing housing coupled to a housing surface of the bearing ring, a first airflow passage through the bearing ring, a cooling entrance pathway, and/or a cooling exit pathway. The bearing housing may comprise a first passage inlet configured to allow a cooling airflow. The first airflow passage may comprise a first passage outlet, may be aligned with the first passage inlet, and may be configured to allow the cooling airflow. The cooling entrance pathway may extend from a first engine airflow channel to the first passage inlet. The cooling exit pathway may extend from the first passage outlet to a second engine airflow channel.

Abstract: A cooled wall of a turbine component includes a first layer of channels for a coolant arranged along a side of the wall facing to a flow of hot gas, the first layer of channels having a serpentine shape, each channel of the first layer having an inlet and an outlet; a second layer of channels for the coolant disposed further from the flow of hot gas than the first layer, each channel of the second layer having an inlet and an outlet, the outlet of each of the channels of the first layer being in fluid communication with corresponding inlet of associated channel of the second layer creating a bend for changing a direction of the coolant leaving the channel of the first layer when entering the channel of the second layer.

Abstract: The internal combustion engine is provided which may include a cylinder head, a turbine, and a turbine housing. The turbine housing may include an exhaust gas passage, at least one coolant fluid passage, and a wall between the passages. The wall may have a first area (Aexhaust) disposed to absorb heat from an exhaust flow passing through the exhaust gas passage, and a second area (Acoolant) disposed to transfer heat from the wall to be absorbed by a coolant fluid flow passing through the at least one coolant fluid passage, wherein the following applies: Acoolant/Aexhaust?1.2.

Abstract: A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference system based on the second element.

Abstract: A vane (18) has an airfoil section (19) that extends in a radial direction and an outer shroud (20) that is disposed on the radially outward side of the airfoil section (19), and is supported inside a casing by means of a vane support member (24). The outer shroud (20) has a shroud body (31), radial protrusions (36, 37), and a hook section (32) including the radial protrusions (36, 37) and engaging parts (39, 40). A recessed part (50), which is recessed in an axial direction or in the radial direction, is provided in at least a part of the circumference of the hook section (32). The engaging part (39) has a sealing surface that continues along the entire circumference thereof, the sealing surface coming into contact with the vane support member (24) in the radial direction.

Abstract: A turbomachine having a wall that extends circumferentially to a central axis of the turbomachine at least in certain areas, and having at least one insert device that can be connected in a releasable manner to a wall in the area of a recess which is arranged inside the wall. The insert device has a connection device by means of which the insert device can be brought into operative connection with a connection device of the wall. The connection device of the insert device has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that in the mounted state of the insert device meshes in a groove of the connection device of the wall. The connection device of the wall has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that, in the mounted state of the insert device, meshes in a groove of the connection device of the insert device.

Abstract: Aspects of the disclosure are directed to a first device coupled to a bearing compartment structure, a second device coupled to an engine case structure, and a controller. The controller is configured to: issue a command to one of the first device or the second device to generate a signal, obtain data from the other of the one of the first device or the second device, where the data is based on the signal, process the data to determine that a skew exists between the bearing compartment structure and the engine case structure in an amount that is greater than a threshold, identify at least one torqueing device to activate based on processing the data, and cause the at least one torqueing device to activate to cause the bearing compartment structure and the engine case structure to align within the threshold amount.

Abstract: An exhaust frame includes: an inner casing; an inner diffuser which defines, between the inner diffuser and the inner casing, an annular inner cooling passage connected to a final-stage wheel space; an outer diffuser which defines an exhaust passage between the outer diffuser and the inner diffuser; an outer casing which defines an annular outer cooling passage between the outer casing and the outer diffuser; a strut which connects the inner casing and the outer casing to each other while crossing the exhaust passage; a strut cover which connects the inner diffuser and the outer diffuser to each other, and defines, between the strut cover and the strut, an annular connection passage connecting the inner cooling passage and the outer cooling passage to each other; and a communication hole provided in a wall of the outer cooling passage at a position on the downstream side of a center line of the strut in the flow direction of a combustion gas.

Abstract: A damper assembly for minimizing heat loss through an exhaust stack includes a housing mountable within the stack and an umbrella received within the housing. The umbrella is selectively movable between a first position in which the umbrella is received within the housing, and second position in which the umbrella is extended from the housing such that a peripheral edge of the umbrella is in close association with an interior sidewall of the exhaust stack to minimize a flow of fluid past the umbrella and out of the stack.

Abstract: A damper assembly for minimizing heat loss through an exhaust includes a housing mounted within the stack and a bladder received within the housing. The bladder is selectively movable between a first position in which the bladder is deflated and received within the housing, and second position in which the bladder is positioned outside the housing and inflated such that a peripheral surface of the bladder contacts an interior sidewall of the stack to create a gas seal.

Abstract: The purpose of the present invention is to decrease the loss of energy of flue gas when superheated steam is cooled and prevent heat efficiency from being decreased. A boiler is provided with: economizers (a medium-pressure economizer (13) and a high-pressure secondary economizer (18)) which heat water supplied by water supply pumps (a medium-pressure water supply pump (27) and a high-pressure water supply pump (28)); evaporators (a medium-pressure evaporator (16) and a high-pressure evaporator (21)) which evaporate the water that is heated by the economizers; and cooling devices (a medium-pressure system and a high-pressure system) which mix water, as a coolant, which has passed through the economizers via the water supply pumps with steam.

Abstract: A fluid expander is disclosed as used in conjunction with an air compressor that is driven by a prime mover. The fluid expander is structured to extract useful work from a fluid stream and add that work to the work provided by the prime mover to the compressor. In some embodiments a clutch can be used to decouple the expander from the compressor if insufficient work is developed by the expander. A gear train can also be used to change the rotational speed prior to work being delivered to the compressor.

Abstract: A lever for the valve actuation of an internal combustion engine, which is mounted such that it can pivot about an axis and has a contact surface for a valve stem end and a contact surface for a cam of a camshaft, is formed as a sheet metal rocker lever having an inverse U-shaped base including a top section and two parallel side walls integral thereto, wherein the axis is arranged at one longitudinal end of the lever, and a valve contact lug having the contact surface for the valve stem end is arranged at the other longitudinal end.