Abstract: The present invention relates to an impingement cooling mechanism (1) that ejects a cooling gas (G) toward a cooling target (2) from a plurality of impingement holes (4) formed in an opposing member (3) that is arranged opposite the cooling target (2). Turbulent flow promoting portions (6) are provided in the flow path of a crossflow (CF), which is a flow that is formed by the cooling gas (G) after being ejected from the impingement holes (4). The turbulent flow promoting portions (6) are constituted so that a turbulent flow is promoted from the upstream side to the downstream side of the crossflow (CF).

Abstract: A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

Abstract: A flow path component for a gas powered turbine includes a flow path component body having cross sectional profile having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a first side and by a second side opposite the first side. A serpentine cooling passage includes a plurality of segments, each of the segments being generally radially aligned. A first subset of the segments is disposed along one of the first side and the second side of the cross sectional profile, and a second subset of the segments spans the flow path component body from the first side to the second side. A cavity is positioned internal to the flow path component body. The cavity is at least partially shielded from one of the first side and the second side by at least one of the plurality of segments.

Abstract: An engine component with particulate mitigation features is provided. The engine component comprises an internal engine component surface having a cooling flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall.

Abstract: A removably attachable snubber assembly for turbine blades includes a turbine blade airfoil including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface extending in a radial direction to a tip. At least one snubber attachment platform is integrally formed onto the outer surface of the turbine blade airfoil. The at least one snubber attachment platform includes an interlocking mechanism. A snubber is removably attachable to the at least one snubber attachment platform, the snubber including a first end, a second end, a trailing edge, a leading edge, a snubber length, and a snubber width. The snubber also includes a removable attachment mechanism on at least one of the first end and the second end that connects with the interlocking mechanism on the at least one snubber attachment platform.

Abstract: A method is disclosed for manufacturing a blade tip coating. The blade tip coating (152) comprising an abrasive (156) and a matrix (154). The method comprises forming a mixture comprising the abrasive, a precursor of the matrix, and an additional particulate (158). The mixture is pressed, the additional particulate acting as a stop to limit thickness reduction of the mixture.

Abstract: A heat shield is provided for use in an inner cavity of a gas turbine engine component. The heat shield comprises a heat shield body comprising opposed side portions defining an inner channel. An inner section of a side portion of the opposed side portions is inwardly sloped such that a cross-section of the heat shield body is smaller in an inner body portion relative to a cross-section of an outer body portion thereof. An aperture is disposed through the side portion in a selected radial position. A vane assembly including the heat shield is also provided.

Abstract: An airfoil for a gas turbine engine includes first pressure and suction side layers forming a cavity and terminating in ends near a trailing edge. The first and second suction side layers are constructed from a composite material. A bridge is wrapped about the ends.

Abstract: An asymmetric twin scroll turbine 10 combined with an integrated exhaust manifold cylinder head 20 may be designed to accommodate mixed, radial or axial flow turbines. The asymmetric twin scroll turbine 10 includes a first scroll 11 and second scroll 12 wherein the first scroll 11 is larger and has greater mass flow capacity than the second scroll 12. The larger volute increases flow capacity and counteracts backpressure creating evenly balanced or equalized peak pressures and pulsations between both volutes and balancing of gas flow between cylinder sets. By equalizing peak pressures, pulsations, and gas flow between cylinder sets, engine self-ignition can be avoided in the cylinder set that would have had the largest peak pressures and pulsations. By in creasing flow capacity of the larger volute and balancing gas flow between cylinder sets, the turbine pressure differential is reduced and the engine can operate more efficiently, improving fuel economy.

Abstract: A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.

Abstract: A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.

Abstract: A brush seal land is disclosed. The brush seal land may comprise a first portion configured to be coupled to a turbine disc of an aircraft engine and a second portion having a contact surface. The brush seal land may comprise a concave annular structure. The second portion may deflect through a clearance area in response to contact with a brush. The second portion may not deflect in response to contact with a brush after the second portion has deflected through a clearance area in response to contact with the brush. The contact surface comprises tungsten carbide. The brush seal land may comprise INCONEL. The brush seal land may be configured to be coupled to an annular member extending from the turbine disc. The brush seal land may reduce abrasion to an annular member extending from the turbine disc by a brush.

Abstract: A stiffness controlled abradeable seal system for a gas turbine engine includes a cantilevered arm that supports one of a rotating seal surface and a static seal surface, a stiffness of the cantilevered arm controlled to achieve a desired operational temperature at a seal interface.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an adjacent second seal section, each including a base and two extending legs defining respective first and second ends of the seal. At least the first seal section includes a first plurality of slots extending from the first end to the base and a second plurality of slots extending from the second end to the base.

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: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centerline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centerline relative to the nominal centerline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centerline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different center-lines.

Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.

Abstract: Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

Abstract: A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.

Abstract: A system includes, in one example, a shroud configured to circumscribe a plurality of rotor blades of a gas rotor engine, and at least one rub button including a head portion having a height configured to extend into a flow path region of the shroud along a central axis of the rub button that extends radially into the flow path region. The head portion includes a profile, orthogonal to the central axis, that varies according to a defined function of the height of the head portion.

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract: A titanium alloy may be characterized by a good oxidation resistance, high strength and creep resistance at elevated temperatures up to 750° C., and good cold/hot forming ability, good superplastic forming performance, and good weldability. The alloy may contain, in weight percent, aluminum 4.5 to 7.5, tin 2.0 to 8.0, niobium 1.5 to 6.5, molybdenum 0.1 to 2.5, silicon 0.1 to 0.6, oxygen up to 0.20, carbon up to 0.10, and balance titanium with incidental impurities.

Abstract: A tank device of an aero engine, which has an inlet appliance for the supply of an air-oil volume flow into a tank space of the tank device, a separation appliance for the separation of oil from the air-oil volume flow that is supplied to the tank space, a conduit area which is confined by at least one wall and in which an air-oil volume flow can be guided in the area of the tank space at least in certain areas, and an outlet appliance, in the area of which a volume flow can be discharged via a valve appliance from the tank space of the tank device. At least one appliance for introducing oil is provided, by means of which oil can be supplied into the area of the conduit area substantially against a flow direction of the air-oil volume flow which is forming during operation in the conduit area.

Abstract: The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. Moreover, the inside surface of the first guiding edge forms a shoulder for guiding the rolling element, the through-hole defining a lubricant drainage orifice.

Abstract: A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed.

Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.

Abstract: A method of supporting a cantilevered component prior to machining the cantilevered component, wherein the cantilevered component is mounted on a hub, the method comprising the step of providing an adhesive carrier, applying adhesive to the carrier and adhering the carrier to the cantilevered component and allowing the adhesive to cure. The carrier may rigid and braced against adjacent blades or against another carrier located on an opposing side of the aerofoil. Alternatively, the carrier may be a flexible fabric that can be wrapped around the blade. Advantageously, the blade can be machined through the carrier.

Abstract: A control method for optimizing a turndown operation for a power plant having a plurality of generating units. The plurality of generating units each may include either an on-condition or an off-condition during a selected operating period.

Abstract: A power generation system includes a first on-off valve that, with respect to a maintenance target device including at least one of a circulation pump, an evaporator, an expander, and a condenser in a medium circuit through which a medium with a boiling point lower than that of water circulates, is on an upstream side in a flow direction of the medium in the medium circuit, and is capable of shutting off the flow of the medium; a second on-off valve that is on a downstream side in the flow direction of the medium in the medium circuit, and is capable of shutting off the flow of the medium; a port that is communicable with the medium circuit between the first on-off valve and the second on-off valve; and a third on-off valve that is in the port.

Abstract: To effectively reduce a situation in which an over-rotation of an expander occurs or the expander becomes a load on an engine at the time of a stop of a Rankine cycle in an exhaust heat recovery device provided with the Rankine cycle that recovers exhaust heat of an engine. A pressure difference ?P between a high-pressure side and a low-pressure side of the Rankine cycle is obtained when the Rankine cycle is stopped (S1), a waiting time Ta is set (calculated) based on the obtained pressure difference ?P (S2). Then, a bypass valve is opened to allow a refrigerant to circulate while bypassing the expander (S3), and then an electromagnetic clutch is disengaged when the waiting time Ta has elapsed to block transmission of power between the expander and the engine (S4, S5).

Abstract: A lifter structure includes a cylindrical member configured to be reciprocally slid in a guide hole of a lifter guide according to rotation of a cam and having an engagement groove and a rotation-preventing member which is separate from the cylindrical member and is disposed so as to face an interior of the guide hole. The rotation-preventing member is inserted into the engagement groove to abut against a groove edge of the engagement groove in a rotation direction of the cylindrical member, thereby preventing the cylindrical member from rotation in the guide hole.

Abstract: A method for manufacturing a sliding tappet of a valve train of an internal combustion engine may include the steps of: providing a main body; applying a coating at least on a contact surface of the main body configured for contacting an associated cam. The coating may include tungsten carbide and cobalt, and the coating may be applied via high velocity oxygen fuel spraying. The method may further include the step of performing a surface finishing on the coating after the coating is applied.

Abstract: A cam follower for operable attachment to a valve lifter assembly for use with a variable cam lobe camshaft in a variable valve timing system includes a housing with a central cavity and a mushroom head with a stem pivotably connected to the housing in the central cavity, the mushroom head having a radiused surface for contacting a cam lobe surface. The cam follower is used in combination with a variable cam surface of an axially displaceable camshaft to obtain improvements in idling speed and volumetric efficiency.

Abstract: A camshaft adjuster having a drive element, an output element and a spring, wherein the drive element and the output element can rotate relative to each other, wherein the spring is secured by a spring bearing of the drive element and a spring bearing of the output element, wherein the spring supports the relative rotation between the drive element and the output element, wherein the spring bearing has a radius that is larger than the radius of the spring and, as a result of this ratio of the radii, a two-line contact between the spring and the spring bearing is formed.

Abstract: A method of controlling a lock pin of a CVVT (continuous variable valve timing) system is provided. The method includes an oil supply operation of operating a spool of a valve bolt by means of oil drawn into the CVVT system and supplying the oil to the lock pin and a switching valve. The method further includes a switching-valve opening operation of opening the switching valve by means of pressure of the oil supplied in the oil supply operation, and a lock-pin releasing operation of supplying oil to a chamber when the switching valve opens and releasing the lock-pin when there is no difference in oil pressure between an advanced chamber and a retracted chamber.

Abstract: Provided are a variable valve timing mechanism, an oil pump supplying oil to a hydraulically-actuated device including the variable valve timing mechanism, and a hydraulic control valve which controls oil pressures supplied to a locking mechanism (which includes a locking member configured to fix a phase angle of a camshaft relative to a crankshaft) of the variable valve timing mechanism, an advanced angle chamber and a retarded angle chamber. While an oil pressure in a hydraulic path detected by a hydraulic sensor increases, a hydraulic control valve controller adjusts a degree of opening of a hydraulic control valve according to the detected oil pressure at a time of releasing the locking member from a locking state, to reduce the oil pressure to be supplied to the advanced angle chamber or the retarded angle chamber used to change the phase angle of the camshaft relative to the crankshaft.

Abstract: A sprocket assembly which is either driven by a drive chain or which drives the drive chain includes a hub centered about a sprocket axis and defining a hub radially outer surface; a plurality of sprocket teeth extending radially outward from the hub; and a cushion ring assembly adjacent to the plurality of sprocket teeth and circumferentially surrounding the hub radially outer surface. The cushion ring assembly includes a cushion ring adjacent to the plurality of sprocket teeth and circumferentially surrounding the hub radially outer surface; the cushion ring being resilient and compliant. The cushion ring assembly also each includes a retention ring which is partially embedded within the cushion ring and which engages the hub radially outer surface in an interference fit, the retention ring providing axial and radial retention of the cushion ring to the hub.

Abstract: A camshaft phaser includes an input member; an output member defining an advance chamber and a retard chamber with the input member; a camshaft phaser attachment bolt which clamps the camshaft phaser to a camshaft, the camshaft phaser attachment bolt having a bolt valve bore extending along an axis. A valve sleeve is located coaxially within the bolt valve bore such that an annular clearance is provided radially therebetween. A valve spool is located coaxially within the valve sleeve such that the valve spool is moved coaxially between an advance position and a retard position. A compliant sealing ring radially between the bolt valve bore and the valve sleeve prevents fluid communication through the annular clearance axially between opposing axial sides of the sealing ring and isolates the valve sleeve from radial expansion of the camshaft phaser attachment bolt.

Abstract: A valve for a valve device may include a valve stem, which in an axial direction relative to a valve stem axis merges into a valve disc projecting from the valve stem radially. A valve cap may be included composed of a metal. The valve cap may be attached to an axial end portion of the valve stem facing away from the valve disc. The valve cap may cover a face end of the valve stem facing away from the valve disc and may envelope the axial end portion of the valve stem at least partially.

Abstract: An intake valve for an internal combustion engine is provided. The intake valve includes a valve stem with a hole in the valve stem forming an air channel there through that allows intake air to flow from an intake passage, through the air channel, into a cylinder of the internal combustion engine.

Abstract: A hydraulic valve brake for a hydraulic valve drive of an internal combustion engine is provided. The valve brake includes a housing with a housing wall and with a housing base, and includes a piston which moves axially in the housing and one end side of which, together with the housing wall and the housing base, delimits a hydraulic pressure chamber and the other end side of which actuates a gas exchange valve. The housing wall is perforated in the region of the pressure chamber by one or more overflow openings, the opening cross sections of which are controlled by a control edge, which delimits the end side at the pressure chamber side, of the piston. In this case, it is the intention for the axial distance (h) between the control edge of the piston, when the latter is fully retracted into the housing, and the housing base to be set by a spacer of predetermined thickness (d).

Abstract: An oil deterioration suppressing apparatus for an internal combustion engine comprises a first oil filter and a second oil filter, wherein the first oil filter comprises a first filter member for filtering oil from an oil pan in which oil is stored, and the second oil filter comprises a second filter member for filtering oil from the oil pan, and wherein the second filter member is made of a ceramic material and has a mean pore size smaller than the mean pore size of the first filter member.

Abstract: A magnetic drain plug includes a plug body that has a head section and a screw section protruding from the head section. The screw section is includes external threads for threading into a drain hole of a device containing lubricating fluid. The plug body has an axial bore for receiving a removable magnet through the head section. The axial bore has an axial depth such that a bottom of the axial bore extends into the screw section.

Abstract: An oil separator may be used in a variety of contexts, one of which is for crankcase ventilation of an internal combustion engine. The oil separator may include a hollow member that extends along a longitudinal axis and is configured to receive a gas flow that is charged with oil. The oil separator may also include an oil separation member disposed within the hollow member and against which the gas flow flows. A redirection member may be disposed proximate the oil separation member in the hollow member, wherein the redirection member redirects at least a portion of the gas flow traveling substantially along the longitudinal axis radially outwards so as to impact an inner side of the oil separation member. As a result of an impactor effect from the gas flow striking the oil separation member as well as the inertia of the oil, the oil may remain in and/or pass through the oil separation member.

Abstract: A honeycomb filter includes a honeycomb structure body having porous partition walls defining a plurality of cells, inflow side plugging portions, and outflow side plugging portions, and in a cross section perpendicular to a cell extending direction, the whole periphery of each of outflow cells is surrounded by an inflow cell group, inflow cells are defined by inflow/outflow partition walls which are the partition walls defining the outflow cell and inflow/inflow partition walls which are the partition walls intersecting the inflow/outflow partition walls, a surface area A1 of the inflow/outflow partition wall of the inflow cell and a surface area A2 of the inflow/inflow partition wall of the inflow cell satisfy a relation of 1.2?A1/A2?2, and in the partition wall, an average pore diameter of a surface region is from 4 to 60% of an average pore diameter of a central region.

Abstract: A spindle assembly of a secondary heater for a diesel exhaust fluid tank having a primary heater, the spindle assembly including a spindle having a first end and a second end opposite the first end, the first end and the second end defining a central axis therebetween, the spindle defining a plurality of grooves arranged between the first end and the second end. The spindle assembly includes a retaining pin coupled to the spindle, the retaining pin extending generally parallel to the central axis. The spindle assembly further includes an attachment mechanism coupled to the second end, the attachment mechanism configured to couple the spindle to an inner surface of the diesel exhaust fluid tank. The spindle and the retaining pin are configured to secure a heating wire within the plurality of grooves between the retaining pin and the central axis.

Abstract: An exhaust conduit for a marine exhaust system includes an inlet end portion connectable to an exhaust manifold, an outlet end portion that directs exhaust gases toward an exhaust system outlet, a catalytic converter assembly arranged between the inlet and outlet end portions, and inner and outer tubes. The inner tube directs exhaust gases from the exhaust manifold to the catalytic converter assembly, and the outer tube surrounds the inner tube to define a cooling liquid passage between the inner and outer tubes. A flange is secured to the inner and outer tubes at inlet ends thereof, the flange being connectable to an outlet of the exhaust manifold. The inner tube has a uniform diameter between the flange and the catalytic converter assembly, and is welded to the flange independently of the outer tube. First and second welds join the inner and outer tubes to the flange at radially inner and outer faces, respectively, of a flange rim.