Abstract: A cutting apparatus suitable for creating tunnels and subterranean roadways includes independently pivoting supports that each carry a respective independently pivoting arm and a rotatable cutting head. Each cutting head via the supports and arms, is configured to slew laterally outward in a sideways direction and to pivot in a vertical upward and downward direction. The supports and arms are mounted on a linear moving sled carried by a main frame.

Abstract: The objective of the present invention is to provide a scroll-type fluid machine and maintenance method for same with which reliability and workability are improved by making it possible to supply sufficient grease to necessary parts of an orbiting bearing or auxiliary crank bearing without entailing a complicated operation during maintenance.

Abstract: A method for measuring load performance of a positive displacement motor (PDM) test coupon. The test coupon comprises a partial length of a PDM stage and is received inside a sealable test chamber. In some embodiments, the test coupon may be cut from a failed PDM stage. The test chamber is filled with test fluid. In some embodiments, the test fluid may be drilling fluid sampled from a live well. Rotation of the rotor on the test coupon actuates rotation of the stator. A braking torque is applied to the stator rotation, enabling evaluation of, for example, fatigue load performance of test coupon. Additional embodiments comprise the rotor axis and the stator axis being offset in order to simulate rotor/stator eccentricity in a full size PDM stage.

Abstract: A boundary layer turbine comprising a housing having an inlet and an outlet, the inlet receives a flow of pressurized fluid; a shaft extending longitudinally through the housing and journaled for rotation about its longitudinal axis relative to the housing; a plurality of nested cylindrical tubes of progressively wider diameter arranged coaxially about the shaft and connected to the shaft, wherein adjacent tubes define a cylindrical fluid passageway there-between that is in fluid communication with the inlet and the outlet, thereby the plurality of tubes define a plurality of passageways; at least one nozzle coupled to the inlet configured to direct the flow of fluid from the inlet into the plurality of passageways and against the plurality of tubes at an angle to a normal plane to the curvature of the plurality of tubes and at an angle to the longitudinal axis of the shaft, wherein the angled flow of fluid imparts rotation to the plurality of tubes and the shaft and flows towards the outlet where the fluid i

Abstract: A method of repairing a blisk having a hub with circumferentially spaced blades. The method can include removing a portion of a blade and replacing the portion with a replacement piece. The method can further include welding the replacement portion to the blade. The method can further include at least one of inspecting the weld after the completion of the weld and prior to heat treatment, dimensionally inspecting the replacement piece after machining, peening the blade, and surface finishing the replacement piece.

Abstract: The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

Abstract: The subject matter of the present disclosure can help provide solutions to problems associated with eccentricities between mounting components in rotating gas turbine engine components, such as by providing a simulator component for balancing with an actual component outside of a gas turbine engine installation. The simulator component can allow for balancing of the actual component cumulatively with the simulator component for later installation of the actual component into a gas turbine engine with a simulated component simulated by the simulator component. The simulator component can have rotational dynamic properties, e.g., the same center of gravity and a scaled diametral moment of inertia, relative to the simulated component.

Abstract: A turbine engine, such as a gas turbine engine for an aircraft, can include a compressor section, a combustion section, and a turbine section in axial arrangement. The compressor and turbine sections can include a rotating disk having a plurality of blades and a stationary band having a plurality of stationary vanes. The disk and band are spaced axially defining a buffer cavity. One or more extensions extend into the buffer cavity to prevent ingestion of heated gas into the buffer cavity. Recesses on the underside of the extensions can improve the heat transfer coefficient for the extensions.

Abstract: A liquid ring pump includes a stationary housing that defines an inner space, and a drive shaft rotatably mounted within the stationary housing. The drive shaft defines a rotational axis. An impeller includes a plurality of blades extending radially outward with respect to the rotational axis, and each blade includes a root and a tip, wherein a continuous curve extends from the tip of each blade through the root of the blade and intersects with the rotational axis.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

Abstract: An axial fan includes a motor, an impeller and a hub of the impeller for connecting to a shaft of the motor. A bottom wall of the hub has a central portion, and an outer annular portion connected to the central portion by an intermediate portion defined by a plurality of blades arranged radially and angularly distributed about an axis of rotation. The blades are elasto-plastic blades and are able to prevent the impeller from moving axially parallel to the axis, moving radially perpendicular to the and a bending of the impeller with movements normal to the plane in which the mean surface of the impeller itself lies. The blades allow a movement with torsional bending around the axis to allow the damping of the resonance frequencies of the assembly formed by the impeller-shaft-rotor.

Abstract: A cooling assembly includes a cooling chamber disposed inside of a turbine assembly. The cooling chamber directs cooling air inside an airfoil of the turbine assembly. The cooling assembly includes a metered channel fluidly coupled with the cooling chamber. The metered channel directs at least some of the cooling air out of the cooling chamber outside of a rail surface of the airfoil. The metered channel is elongated along and encompasses an axis. The metered channel has an interior surface with a distance between opposing first portions of the interior surface. The distance between the opposing first portions decreases at increasing distances along the axis from the cooling chamber toward the rail surface.

Abstract: A component for a gas turbine engine, the component having: a cooling slot located on a surface of the component, the cooling slot being defined by a plurality of diffuser portions each extending from a respective one of a plurality of cooling openings providing cooling fluid to the cooling slot.

Abstract: An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.

Abstract: The present disclosure is directed to a blade for a turbomachine. The blade includes an airfoil having a pressure side surface and a suction side surface extending from a leading edge to a trailing edge. The airfoil defines a camber line positioned between the pressure side surface and the suction side surface and extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and defines a cooling cavity therein. The cooling cavity includes one or more turbulators positioned in one or two regions of a forward region, a central region, and an aft region.

Abstract: There is disclosed a component (100,200) for a gas turbine engine (10). The component comprises first (23) and second (24) opposing aerodynamic surfaces with a trailing edge surface (36) therebetween. The trailing edge surface (36) forms a tapered trailing edge section (35) of the component. The trailing edge surface (36) is provided with one or more cooling openings (38) for ejecting a cooling fluid flow.

Abstract: The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (24) extending opposite the pressure-side walls (16) and suction-side walls (14), the outer skin (24) and the wall of the facing blade (12) being separated by an air gap (30), a series of reinforcements (25) formed in the closed wall (22) and leading into the outer skin (24), and a series of through-openings formed in the reinforcements (25), the heights of impact (h) between said through-openings and the pressure-side wall (16) or the facing suction-side wall (14) being greater than the air gap (30).

Abstract: A preform CMC article is disclosed comprising an interior ply structure having at least one interior CMC ply including at least one longitudinal CMC ply disposed along the article length, an exterior shell ply forming an article surface and having at least one exterior CMC ply substantially surrounding the interior ply structure, and at least one wicking portion in which the interior ply structure penetrates the exterior ply shell with an exposed edge of the longitudinal CMC ply disposed at the article surface. A CMC article is disclosed including the interior ply structure and the exterior ply shell, wherein the longitudinal CMC ply includes an exposed edge disposed at the surface of the CMC article. A method for forming the CMC article is disclosed including wicking a melt infiltration agent into the article through the wicking portion into the interior ply structure along the longitudinal CMC ply.

Abstract: An abrasive coating for a substrate comprises a strike layer is formed on a substrate top surface; a base layer is coupled to the strike layer; a tack layer is coupled to the base layer, wherein the tack layer is configured to adhere first grit particles to the base layer; a plurality of first grit particles are adapted to be coupled to the tack layer, a plurality of second grit particles are placed between each of the plurality of first grit particles, the second grit particles having a nominal size smaller than the first grit particles; and an overplate layer comprising a matrix material is bonded to the tack layer; the matrix material envelops the second grit particles and bonds and partially surrounds the first grit particles, wherein the first grit particles extend above the overplate layer.

Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots having a seal assembly disposed therein. The seal assembly including an intersegment seal including a plurality of seal segments defining one or more end regions. One or more of the plurality of seal segments including at the one or more end regions a plurality of jet holes and a channel having a wire disposed therein, wherein the intersegment seal provides sealing of one or more end gaps defined proximate the one or more end regions in response to the thrust of a flow of pressurized air through the plurality of jet holes.

Abstract: A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member.

Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.

Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.

Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and the front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.

Abstract: A fluid induced instability detection system and method is provided to monitor various vibration characteristics of a turbomachine. The fluid induced instability detection system detects abnormalities in the vibration data and provides an indication of one or more potential faults in the turbomachine.

Abstract: A steam turbine valve drive apparatus in an embodiment includes a piston, a cylinder, a bidirectional pump, a servo motor, and a quick closing mechanism. The cylinder houses the piston in an inner space thereof, the inner space being partitioned by the piston into a first hydraulic chamber and a second hydraulic chamber. The quick closing mechanism executes a quick closing operation of closing the steam valve unit more quickly than the closing operation. Here, the quick closing mechanism executes the quick closing operation by feeding the working oil accumulated in an accumulator to the second hydraulic chamber and draining the working oil from the first hydraulic chamber.

Abstract: A hydraulic driving device for a steam valve includes a plurality of hydraulic actuators to generate driving force to be transmitted to the valve body through a valve shaft of the steam valve. The hydraulic actuators each include a cylinder, a piston that is capable of reciprocating in the cylinder, and a rod having respective ends connected to the piston and valve shaft. The hydraulic actuators include a main actuator including a throttle portion for regulating a flow of pressure oil in a hydraulic chamber defined by the cylinder and piston so that a damping force is applied to the valve body during its closing operation. The one or more hydraulic actuators other than the main actuator include at least one sub actuator not having the throttle portion. The hydraulic chamber of the sub actuator communicates with the hydraulic chamber of the main actuator.

Abstract: In one example embodiment, a fluid induced instability detection system is provided that monitors various vibration characteristics of a turbomachine, collects vibration data in real-time, and uses the vibration data to detect and analyze changes in various operating parameters such as vibration, speed, and loading conditions, and to provide an indication of a vibration anomaly and/or potential operational risk in one or more components of the turbomachine. The vibration data can be particularly associated with certain components that are directly or indirectly impacted by a modification in process fluid flow characteristics or lubrication oil flow characteristics in the turbomachine due to various reasons such as process fluid flow disturbances, lubricating oil flow disturbances, and/or a change in turbomachine operational parameters. The fluid induced instability detection system detects abnormalities in the vibration data and provides an indication of one or more potential faults in the turbomachine.

Abstract: The invention relates to a device (3) for attaching manifolds (1) for cooling the casing (2) of a preferably low-pressure turbine of a turbine engine by air jets, comprising a mounting (4) of said manifolds, shaped such as to keep said manifolds spaced apart from one another and a plurality of elements (5) for supporting said manifold mounting (4), each supporting element being attached to the casing, and connected to said manifold mounting (4) by connection means (6, 6?). Said device is characterised in that it comprises N cooling manifolds (1) and N?1 supporting elements (5), each supporting element (5) being arranged between two adjacent cooling manifolds.

Abstract: A transmission assembly including a transmission member and an oil distribution system. The transmission member includes a rotary pivot, and a pivot portion for pivoting about the rotary pivot; the oil distribution system is to receive oil feed and to transfer it to an oil reception chamber of the rotary pivot; the rotary pivot includes injection orifices putting the oil reception chamber into fluid flow communication with the gap between the rotary pivot and the pivot portion to form a fluid bearing; and the transmission assembly is for injecting oil into the gap at a first pressure into an outer portion of the gap, and at a second pressure into an inner portion of the gap, the second injection pressure being different from the first injection pressure.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes and inner shell and an outer shell. The inner shell includes an inner base portion defining an inlet and a volute portion defining an outer contour of a volute in fluid communication with the inlet. The outer shell circumscribing the volute portion in a radial plane and includes an outer base portion circumscribing the inner base portion. The inner shell includes a first plurality of sheet metal structures joined to one another in the radial plane, the outer shell includes a second plurality of sheet metal structures, and first portions of the second plurality of sheet metal structures surrounding the volute portion are joined to one another in an axial plane transverse to the radial plane.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a bypass valve assembly structure including a guide portion, an inner sheet metal shell including an inner inlet portion and a volute portion providing an outer contour of a volute, wherein an end of the inner inlet portion is surrounded by the guide portion and spaced apart from the bypass valve assembly structure, and an outer sheet metal shell radially surrounding at least a portion of the volute portion and including an outer inlet portion surrounding the inner inlet portion and contacting the guide portion of the bypass valve assembly structure.

Abstract: The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame defines an inner ring and an outer ring generally concentric to the inner ring about the axial centerline. The frame defines a plurality of struts extended outward along the radial direction from the inner ring to the outer ring. One or more struts define one or more service passages extended at least partially along the radial direction within the strut, and wherein the inner ring, the outer ring, and the struts together define an integral structure.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes an inner shell defining an inner inlet portion and a volute portion providing an outer contour of a volute, an outer shell surrounding the volute portion and defining an outer inlet portion circumscribing the inner inlet portion, and one or more energy absorbing members coupled to an inner surface of the outer shell between the outer shell and the inner shell. The inner shell includes a first plurality of sheet metal structures coupled together in a first plane and the outer shell includes a second plurality of sheet metal structures coupled together in a second plane transverse to the first plane.

Abstract: A gas turbine exhaust diffuser is configured to be at least partially disposed within an exhaust collector. The diffuser also includes an inner wall configured to extend to a back wall of the exhaust collector, an outer wall circumferentially disposed about the inner wall along a portion of the collector, and an inlet between the upstream end of the inner and outer walls. The inlet is configured to receive an exhaust flow from a gas turbine engine. An outlet for the exhaust is located between the inner wall and a downstream end of the outer wall. The outer wall is asymmetrically shaped so that an opening between the outlet and the back wall of the exhaust collector is larger on a first lateral side of the diffuser adjacent an exhaust exit of the collector than an opposite lateral side of the diffuser.

Abstract: A system includes a turbine system that contains a heat recovery steam generator (HRSG) having a flow path that receives an exhaust gas, and having a fluid path that receives a fluid. The fluid path is adjacent to the flow path such that the fluid is heated by the exhaust gas. The HRSG includes an electrical heater that provides heat to the fluid path during a start-up mode of the HRSG, during a shutdown mode of the HRSG, or both.

Abstract: The present application provides a power generation system. The power generation system may include a gas turbine engine for creating a flow of combustion gases, a steam turbine, and a steam turbine preheating system. The steam turbine preheating system ay receive an extraction of the flow of combustion gases and delivers the extraction to the steam turbine to preheat the steam turbine.

Abstract: A compact energy cycle construction that utilizes a working fluid in its operation is disclosed having a compact housing of a generally cylindrical form, an orbiting scroll type expander, a central shaft which is driven by the expander, a generator having a rotor and a stator with the central shaft being mounted to the rotor for rotating the rotor relative to the stator, a pump mounted to the central shaft, an evaporator positioned between the expander and the generator and surrounding the central shaft, and the orbiting scroll type expander, the central shaft, the generator, the pump, and the evaporator being housed within the compact housing to form an integrated system operable in accordance with an energy cycle.

Abstract: The present application provides a power generation system. The power generation system may include a gas turbine engine, a steam turbine, and a steam turbine preheating system. The steam turbine preheating system may include a steam generator that creates a flow of steam to preheat the steam turbine from an extraction of the gas turbine engine.

Abstract: Systems and methods are provided for the recovery of mechanical power from heat energy sources via multiple heat exchangers and expanders receiving at least a portion of heat energy from a source. The distribution of heat energy from the source may be portioned, distributed, and communicated to the input of each of the heat exchangers so as to permit utilization of up to all available heat energy. In some embodiments, the system receives heat energy from more than one source at one or more temperatures. Mechanical energy from expansion of working fluid in the expanders may be communicated to other devices to perform useful work or operatively coupled to one or more generators to convert the mechanical energy into electrical energy.

Abstract: A monolithic rocker arm component includes a first lateral wall defining a first aperture and a first mass reducing feature, an opposing second wall defining a second aperture and a second mass reducing feature, a pushrod receiving member that bridges the first lateral wall and the second lateral wall at a first end of the rocker arm, and a tongue element that bridges the first lateral wall and the second lateral wall at a second end of the rocker arm. The pushrod receiving member routes oil from the first towards the second end. The monolithic rocker arm may have one or more internal regions having lattice structures. Methods for additive manufacturing the monolithic rocker component are also provided.

Abstract: A valve train for a reciprocating piston internal combustion engine may include a crankshaft, at least one inlet valve, at least one outlet valve, at least one camshaft coupled rotationally to the crankshaft, at least one inlet cam held on a first camshaft, at least one outlet cam held on one of the first camshaft or a second camshaft, at least one brake cam held on one of the first camshaft or the second camshaft, at least one inlet cam follower, which may actuate the at least one inlet valve and may be drive-connected at least at times to the inlet cam, at least one outlet cam follower, which may actuate the at least one outlet valve, may be drive-connected at least at times to the outlet cam, and, in a braking mode, may be drive-connected at least at times to the brake cam, and a phase shifting device for adjusting a phase position of the brake cam relative to the crankshaft.

Abstract: An electric phaser for dynamically adjusting the phase of a camshaft relative to a crankshaft with a split ring planetary drive. The split ring planetary drive including: a sun gear driven by a motor, a plurality of planetary gears with stop teeth, a first ring gear driven by the crankshaft, and a second ring gear rotatable with the camshaft. Either the first or second ring gears each include a first and a second stop. When the stop teeth of the planetary gears interacts with the first stop or the second stop on either the first or second ring gears, rotation of the phaser further in the first direction or the second direction towards the first or second stops is halted.

Abstract: An electromagnetic linear motor is described. It comprises a tubular stator (1) having a longitudinal axis (W); and a permanently magnet (7) with poles oriented along the axis and linearly movable along said axis inside the stator (1). The stator (1) comprises at least two columns (A, B) formed by electromagnets (2), each electromagnet (2) comprising a core (U) formed by a central straight segment (4) and two end polar expansions (5) all being oriented towards the—and orthogonally to—said axis (W), The columns are circularly arranged around said the permanent magnet (7), and mutually linearly offset along said axis.

Abstract: A valve train for an internal combustion engine may include a cam shaft and a cam follower. The valve train may also include a first cam arranged on the cam shaft for conjoined rotation. The valve train may further include a second cam arranged on the cam shaft for conjoined rotation and axially adjacent to the first cam. The cam follower may be axially adjustable between a first position, in which the cam follower is drive-connected to the first cam, and a second position, in which the cam follower is drive-connected to the second cam. The cam follower may include a mechanical adjustment device interacting with the cam shaft for axially adjusting the cam follower between the first position and the second position.

Abstract: A check valve is described for a gas-carrying line in a motor vehicle, in particular for the venting of a crankcase, having a valve housing which has a valve seat, a valve disk which abuts against the valve seat in a closed position and an electric heating device for heating the valve housing, wherein the valve disk is integrally configured with a spring and fastening section that is fixed to the valve housing and generates a closing force that presses the valve disk against the valve seat, and wherein the valve housing has a metal body, which forms the valve seat and on its outside forms a thermal coupling surface, on which the electric heating device sits and which extends together with the electric heating device beyond the valve seat both in the flow direction and in the opposite direction.

Abstract: An adapter for the intake side of an oil and air separation system, including a first end portion capable of replacing an engine oil fill cap, the first end portion connected to an intermediate portion that removably engages with a second end portion including a hose coupling that allows the adapter to be connected to the intake side of an oil and air separation system via a hose.

Abstract: A device for separation of oil droplets and/or oil mist from blow-by gases of an internal combustion engine is described. Also described is a ventilation system for ventilation of the crankcase of an internal combustion engine, a cylinder head cover and an internal combustion engine, which contain such a device.

Abstract: A device for separation of oil droplets and/or oil mist from blow-by gases of an internal combustion engine. Also described is a ventilation system for ventilation of the crankcase of an internal combustion engine, a cylinder head cover and an internal combustion engine, which contain such a device.