Abstract: In some embodiments, a gamma titanium aluminide alloy consists essentially of, in atomic percent, about 38 to about 50% aluminum, about 6% niobium, about 0.25 to about 2% tungsten, optionally up to about 1.5% boron, about 0.01 to about 1.0% carbon, optionally up to about 2% chromium, optionally up to about 2% vanadium, optionally up to about 2% manganese, and the balance titanium and incidental impurities. In some embodiments, the gamma titanium aluminide alloy forms at least a portion of a gas turbine component. In some embodiments, a gamma titanium aluminide alloy, consisting essentially of, in atomic percent, about 40 to about 50% aluminum, about 3 to about 5% niobium, about 0.5 to about 1.5% tungsten, about 0.01 to about 1.5% boron, about 0.01 to about 1.0% carbon, optionally up to about 2% chromium, optionally up to about 2% vanadium, optionally up to about 2% manganese, and the balance titanium and incidental impurities.

Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform is arranged between the root and the airfoil and is shaped to block gasses from the gas path migrating toward the root when the turbine blade is used in a gas turbine engine.

Abstract: A heterogeneous composition is disclosed, including an alloy mixture and a ceramic additive. The alloy mixture includes a first alloy having a first melting point of at least a first threshold temperature, and a second alloy having a second melting point of less than a second threshold temperature. The second threshold temperature is lower than the first threshold temperature. The first alloy, the second alloy, and the ceramic additive are intermixed with one another as distinct phases. An article is disclosed including a first portion including a material composition, and a second portion including the heterogeneous composition. A method for forming the article is disclosing, including applying the second portion to the first portion.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.

Abstract: A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered projecting from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered projecting from and formed in one piece with the coupling root; an upper connecting fin cantilevered projecting from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.

Abstract: A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a downstream cover plate and a downstream angel wing that extends axially from the downstream cover plate. A portion of the downstream cover plate radially outward of the downstream angel wing defines an approximately linear profile. The turbine blade also includes a dovetail region that extends radially inwardly from the shank. A profile of a portion of the downstream cover plate radially inward of the downstream angel wing is recessed relative to the linear profile.

Abstract: A method of modifying a shank of a turbine blade from an initial profile to an undercut profile includes removing a first portion of material from an underside of a downstream angel wing of the turbine blade. The downstream angel wing extends axially from a downstream cover plate of the shank. The method also includes removing a second portion of material from a generally axially-extending portion of the downstream cover plate adjacent a dovetail of the turbine blade.

Abstract: Described is a turbine arrangement of a gas turbine engine, the turbine comprising: a rotor comprising a disc which incorporates a plurality of circumferentially spaced turbine blades, each blade having an aerofoil extending for a platform and a root portion securing the blade to the disc, a lock plate located at an axial end of the root portion of the blade, the lock plate comprising: a plate body having an inward facing surface which is located adjacent the blade root and an outward facing surface, radially inner and outer edge portions, and first and second circumferential edges; a head located at the radially outer edge portion of the plate body; a foot portion located at the radially inner portion of the plate body; a projection extending from the outwardly facing surface away from the turbine blade root in use, the projection being located adjacent to the foot portion, wherein the foot portion and head portion are located within slots provided at least partially by the disc and turbine blade respectivel

Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar is hollow, and a cover panel is bonded to an outer surface of standoffs to define passages between the cover panel and the spar. Cooling air is fed to the hollow spar through a cooling feed channel defined in the disk or shank portion.

Abstract: A gas turbine engine, a blisk and methods of manufacturing are disclosed. The blisk includes a disk and a plurality of blades. Each blade includes a platform, an airfoil, and a shank portion radially extending between the platform and the disk. The airfoil includes cooling features. Cooling cavities are defined between shank portions of adjacent blades and are in communication to the internal of blades via cooling feed channels. A coverplate is coupled to a downstream side of the blisk to cover the cooling cavities. A plurality of inner tabs extends from an inner edge of the coverplate to securely couple the coverplate to the disk. The disk and the plurality of blades may be integrally formed or casted as a single unit. The platform, the airfoil, and the shank portion may be formed integrally as a single unit and bonded to the disk to form the blisk.

Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of the airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar includes standoffs, and a cover panel is bonded to an outer surface of the standoffs to define passages between the cover panel and the spar. Cooling air is fed through an inlet port formed in a base standoff to the passages of the spar through a cooling feed channel defined in the disk or shank portion.

Abstract: A blade for a ram air turbine includes a pitch rotation connector configured to connect to a pitch rotation device configured to control rotation of the blade about a pitch axis and an airfoil rotationally fixed to the pitch rotation connector. The pitch rotation connector is positioned on the airfoil to reduce pitch dependent moment about the pitch axis such that a maximum pressure moment about the pitch axis is less than a torque supplied to the blade via the pitch rotation device. The position of the pitch rotation connector can be configured to prevent and/or dampen pitch oscillation due to a changing load on the spring and mass governor.

Abstract: An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).

Abstract: There is disclosed a stator vane section for a gas turbine engine. The stator vane comprises an aerofoil, a first platform at a radial end of the aerofoil, a cooling chamber within the aerofoil and a guide duct within the cooling chamber. An impingement chamber is defined between the first platform and a perforated impingement plate provided on the first platform to receive cooling air through the impingement plate. The guide duct is coupled to the first platform so that a collecting chamber extending around the guide duct is defined between the guide duct and the first platform and the collecting chamber is configured to receive cooling air from the impingement chamber via a plurality of collecting channels, and is configured to direct cooling air to the cooling chamber.

Abstract: A turbine engine turbine including a nozzle stage made of ceramic matrix composite material and including a plurality of annular sectors forming an annulus presenting an inner shroud and an outer shroud, each sector having an inner platform forming a portion of the inner shroud, an outer platform forming a portion of the outer shroud, and at least one airfoil extending between the outer and inner platforms and secured thereto. A metal ring includes at least one annular sector, and presents an outer surface in contact with the surface of the inner shroud opposite from the surface from which the airfoils extend, the metal ring presenting an outside diameter at its outer surface that is greater than the diameter of the inner shroud such that the nozzle stage is held in compression between a casing and the metal ring.

Abstract: A shroud segment arranged radially outward of a gas flow path of a gas turbine. The shroud segment includes a body having walls defining an internal pocket for receiving a supply of air. A plurality of pressurization apertures is formed through one of the walls to fluidly connect an internal pocket of the body to an ambient area of the body. A seal slot section is formed in the wall at a position radially inward of the pressurization apertures to receive a seal to connect the shroud segment to an adjacent shroud segment. The pressurization apertures are arranged such that portions of the supply of air are configured to pass through the pressurization apertures and through the seal slot section as leakage into the gas flow path, thereby reducing ingestion of fluid from the gas flow path into the internal pocket of the shroud segment.

Abstract: A shroud assembly for a turbine engine comprises a plurality of circumferentially arranged shroud segments, each terminating in circumferentially spaced first and second shiplap elements, where the first shiplap element of one shroud segment can overlap the second shiplap element of an adjacent shroud segment.

Abstract: An inner shroud segment may include an inner housing and an outer housing. The inner housing may have a radial curve centered relative to an axis with a radial wall and a bottom wall that define a first channel. The outer housing may have a first axial wall, a first circumferential wall, and a second axial wall that define a second channel. The outer housing may also be disposed within the first channel with the radial wall of the inner housing contacting the first axial wall, the first circumferential wall, and/or the second axial wall. A compliant material may be disposed within the second channel and coupled to the radial wall and the first axial wall, the first circumferential wall, and/or the second axial wall.

Abstract: A seal in a gas turbine for sealing a radial gap defined between rotating and stationary structure. The rotating structure may include a row of rotor blades. The seal may include a pad attached to the stationary structure. The pad may include an abradable structure. The pad may further include a liner attached to and covering an outer surface of the abradable structure. The stationary structure to which the pad is attached may define an axial section of the outer radial boundary of the annular flowpath, the axial section coinciding axially with an axial position of the row of rotor blades.

Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.

Abstract: An abradable sealing element is positioned radially outwardly of a plurality of aerofoil blades of a gas turbine engine. The abradable sealing element comprises a radially inwardly facing surface region and a plurality of cooling holes. The radially inwardly facing surface region comprises a wall structure, with the wall structure having one or more radially inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. Each of the inwardly projecting walls is continuous and defines a plurality of repeating units arranged circumferentially around the radially inwardly facing surface region, each repeating unit is open at a radially inwardly facing side of the sealing element, and each repeating unit comprises a plurality of curved portions forming a multi-lobed profile shape. Each cooling hole is provided in the radially inwardly facing surface region at a position within the multi-lobed profile shape.

Abstract: A propulsion system for an aircraft includes a turbomachine having a first turbine, a primary fan mechanically driven by the first turbine of the turbomachine, and an electric generator mechanically driven by the first turbine of the turbomachine. The propulsion system also includes an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly.

Abstract: A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.

Abstract: A turbo rotation sensor includes a magnet magnetized with two different magnetic poles along a circumferential direction about a rotating shaft of a compressor wheel and provided at an end portion of the compressor wheel on the air intake side, and a sensor portion that is housed in a sensor hole formed on the housing, is arranged to face the magnet in a radial direction of the rotating shaft, and includes two magnetic field detecting elements capable of measuring variation in magnetic flux density caused by the magnet. The two magnetic field detecting elements are aligned in a direction parallel to the rotating shaft so that the respective detection axes are parallel to an axial direction of the rotating shaft. The rotational speed of the compressor wheel is detected based on a difference between the magnetic field strengths detected by the two magnetic field detecting elements.

Abstract: A turbocharger includes a turbine wheel, a turbine housing including a waste gate port allowing exhaust gas to flow by bypassing the turbine wheel, and a waste gate valve configured to open and close the waste gate port. The waste gate valve is configured such that a valve body including a valve plate configured to close the waste gate port by abutting against the turbine housing and a valve stem is tilted with respect to a swing arm. A stopper abutting against the valve body when an abutting surface of the valve plate is apart from the turbine housing and the waste gate port is in an open state is disposed in the turbine housing.

Abstract: A waste gate valve for a turbocharger includes a valve body including a valve plate and a valve shaft, a swing arm including a shaft and a lever, a supporting plate fixed to a portion of the valve shaft that protrudes from the lever, and an elastic member clamped between the supporting plate and the lever or between the lever and the valve plate. One of the supporting plate and the lever that clamp the elastic member or one of the lever and the valve plate that clamp the elastic member includes a protruding portion that is positioned closer to the valve shaft than the elastic member or farther from the valve shaft than the elastic member and that protrudes toward the other of the supporting plate and the lever or toward the other of the lever and the valve plate.

Abstract: The present disclosure is direct to a system for regulating a velocity of gases in a turbomachine. The system includes an exhaust section of the turbomachine. The system also includes a damper having an actuator and a restriction. The damper is positioned within the exhaust section and is operable to adjust the velocity of the gases based on a position of the restriction. The system further includes a controller communicatively coupled to the damper. The controller is configured to control the position of the restriction to regulate the velocity of the gases relative to a predetermined velocity range.

Abstract: A turbocharger with at least one axial turbine stage. Separate circumferential sections of the turbine are fed by separate exhaust system runners. The turbine is designed to harness pulse energy. Corresponding engine having cylinders comprising such a turbocharger.

Abstract: A variable nozzle mechanism for a variable capacity turbocharger includes: a first plate having an annular shape; a second plate facing the first plate and having an annular shape, the second plate and the first plate defining an exhaust gas path in between; a plurality of nozzle vanes rotatably supported between the first plate and the second plate; and an annular member inserted on an inner circumference side of the first plate. The first plate includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface, the annular member includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface, and a gap is provided between the first plate and the annular member, the gap extending along a thickness direction of the first plate, from a point between an inner circumference edge of the front surface of the first plate and an outer circumference edge of the front surface of the annular member.

Abstract: A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

Abstract: A method for controlling a gas turbine engine is provided. The method includes determining if a potential icing condition exists, for example, by determining whether a corrected fan speed percentage is below a predetermined fan speed threshold. If a potential icing condition exists, a fuel regulator may operate according to a first control algorithm by restricting the flow of fuel to the engine if the corrected core speed percentage of the core engine exceeds a predetermined core speed threshold. If a potential icing condition does not exist such that the fan section and core engine of the gas turbine engine are operating normally, the fuel regulator may operating according to a second control algorithm that does not include such a hard compressor speed limit.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine component and a lubrication system. The lubrication system directs lubricant through the turbine engine component. The lubrication system includes a wash flow filter.

Abstract: A fan containment case for a gas turbine engine is provided which includes a barrel having an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion. The outermost portion has an outermost band of material made of carbon fiber composite and the innermost portion has an innermost band of material made of carbon fiber composite. The interior portion includes a first interior band and a second interior band adjacent the first interior band. The first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second interior band is made of an aramid material. The innermost portion has an innermost band of material made of carbon fiber composite.

Abstract: Aspects of the disclosure are directed to a system for an engine having an axial centerline, comprising: a diffuser case, a turbine case, and a turbine vane support, where the diffuser case and the turbine case are coupled to one another via a substantially radially oriented flange, where the turbine vane support includes a heat shield for the flange, and where the turbine vane support includes a radially outward projecting tab that couples to the turbine case via a radial interference fit.

Abstract: An apparatus and system for mechanically connecting components are provided. The apparatus includes a mechanical connecting joint that includes a first joint member formed of a material having a first coefficient of thermal expansion (CTE) value, the first joint member comprising a first sidewall, a second opposite sidewall, and a body extending therebetween. The mechanical connecting joint further includes a second joint member formed of a material having a second CTE value, the second CTE being less than the first CTE. The second joint member includes a first leg facing the first sidewall, a second leg facing the second sidewall, and a connecting member extending between the first leg and the second leg. A first gap is formed between the first joint member and the first leg and a second gap is formed between the first joint member and the second leg.

Abstract: A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method.

Abstract: A heat exchange system with at least one heat exchange chamber with heat exchange chamber boundaries which surround at least one heat exchange chamber interior of the heat exchange chamber, wherein the heat exchange chamber boundaries include at least one first opening for guiding in an inflow of at least one heat transfer fluid into the heat exchange chamber interior and at least one second opening for guiding out an outflow of the heat transfer fluid out of the heat exchange chamber interior is provided. At least one heat storage material is arranged in the heat exchange chamber interior such that a heat exchange flow of the heat transfer fluid through the heat exchange chamber interior causes a heat exchange between the heat storage material and the heat transfer fluid.

Abstract: The invention relates to a waste-heat utilisation assembly (1) of an internal combustion engine (50), comprising a working circuit (2) that conducts a working fluid. In said working circuit (2) are arranged, in the direction of flow of the working fluid, a feed pump (6), an evaporator (10), an expansion machine (3) and a condenser (4). The evaporator (10) is also arranged in an exhaust tract (53) of said internal combustion engine (50). Between the evaporator (10) and the condenser (4), an auxiliary line (2b) is connected in parallel to the working circuit (2). According to the invention, a sub-stream evaporator (12) is arranged in the auxiliary line (2b) and a pressure sensor (14) and/or a temperature sensor (13) are also arranged in said auxiliary line (2b), said pressure sensor (14) and/or temperature sensor (13) being arranged downstream of the sub-stream evaporator (12).

Abstract: A method and a device may be used to assemble an adjustable camshaft that includes a shaft segment with an inner shaft that extends concentrically through a through-hole of an outer shaft. The method may involve prepositioning the inner shaft by at least partially introducing the inner shaft eccentrically into the through-hole of the outer shaft. The method may further involve introducing a positioning element in an introduction direction through a first outer shaft hole formed in a peripheral wall of the outer shaft, through an inner shaft hole that extends orthogonally to a longitudinal axis of the inner shaft, and through a second outer shaft hole formed in a peripheral wall of the outer shaft such that the positioning element projects out of the second outer shaft hole. Further, the inner shaft may be finally positioned, wherein the positioning element is moved counter to the introduction direction such that the inner shaft is orientated concentrically inside the through-hole of the outer shaft.

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, and a second cam for conjoined rotation, arranged on the cam shaft 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 also 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 continuously variable valve lift system includes a driving swing arm, a camshaft, a valve structure, a middle shaft, an adjusting member and an adjusting swing arm. The driving swing arm, the adjusting member and the adjusting swing arm are sleeved on the middle shaft and are respectively capable of swinging around the middle shaft. The first connecting part, the second connecting part and the third connecting part are arranged sequentially along a circumferential direction of the middle shaft. The second connecting part is located between the first connecting part and the third connecting part, and two sides of the second connecting part abut against the first connecting part and the third connecting part, respectively. The second connecting part abuts against the third connecting part to form a spiral surface therebetween. The adjusting member is further capable of sliding along an axial direction of the middle shaft.

Abstract: A method of phasing the opening and closing of internal combustion engine intake and exhaust valves relative to the rotation of the crankshaft is based upon changes in engine speed, engine load and ambient relative humidity. During certain conditions of higher humidity, in order to maintain good combustion stability and thus overall engine operation, it is necessary to reduce intake and exhaust valve overlap by adjusting the phase of the intake and exhaust camshafts. This is achieved by utilizing a set of cam position reference values and constraints based upon engine speed, engine load and humidity that are contained in lookup tables that adjust and limit cam position and valve overlap. Generally speaking, in order to maintain optimum engine performance, intake and exhaust valve overlap is reduced with higher ambient humidity and vice versa.

Abstract: A system and method of controlling an angular position of a camshaft relative to an angular position of a crankshaft includes detecting rotational movement of an electric motor output shaft controlling a camshaft phaser; detecting rotational movement of the crankshaft; determining the relative difference between the rotational movement of the electric motor output shaft and the rotational movement of the crankshaft; and determining whether the angular position of the camshaft relative to the angular position of the crankshaft is advancing, retarding, or remaining constant.

Abstract: A pulley for phaser including a toothed outer circumference for accepting a drive force; an inner circumference with at least a first set of lands extending towards a center of the pulley and spaced apart along the inner circumference of the pulley; and an axial retaining feature on the first set of lands for interaction with a corresponding retaining feature of a housing press fit within the inner circumference with the pulley, axially retaining the housing within the pulley.

Abstract: A hydraulic fluid system for a variable valve train system is provided that allows hydraulic fluid flow from a high pressure chamber to a medium pressure chamber during a higher pressure phase after a control valve closes. The hydraulic fluid system includes a housing defining (a) the middle pressure chamber which is connected to a hydraulic fluid supply, and (b) the high pressure chamber which contains hydraulic fluid that is pressurized by a pump piston assembly configured to engage a rotating cam. A control valve selectively provides a first flowpath for hydraulic fluid between the middle pressure chamber and the high pressure chamber. A bypass valve selectively provides a second flowpath for hydraulic fluid between the middle pressure chamber and the high pressure chamber based on a pressure of the hydraulic fluid in the high pressure chamber.

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: In a system that selects a large-cam as a driving cam at a time of a start of an engine, when an engine stop request is output, it is determined whether there is a small-cam cylinder for which a small-cam is selected as the driving cam. In a case where it is determined that there is a small-cam cylinder, a switching command for switching the driving cam from the small-cam to the large-cam is output. When an engine start request is output, the above determination is performed again. In a case where it is determined that there is a small-cam cylinder, the switching command is output to all solenoid actuators again. In addition, the drive of the fuel injector is suspended until the switching operation of the driving cam is completed for all cylinders.

Abstract: A variable displacement vane pump with electronic oil pressure control provides efficient pumping of engine oil precise regulation of engine oil pressure. The variable displacement oil pump includes a rotor supported in a housing for rotation about an axis of rotation and a slide ring movably supported in the housing. A plurality of vanes extends between the rotor and the slide ring to define a plurality of variable displacement pumping chambers. An electronic drive mechanism is configured to position the slide ring with respect to the axis of rotation, and a controller is configured to drive the electronic drive mechanism for selectively positioning the slide ring to adjust an eccentricity of the slide ring relative to the axis of rotation such that the displacement of the pumping chambers is varied.

Abstract: An internal combustion engine has a lower link rotatably mounted to a crankpin of a crankshaft, an upper link having a first upper link end rotatably connected to a piston pin of a piston and a second upper link end rotatably connected to a first lower link end side of the lower link through a first connecting pin, and a control link having a first control link end supported on a cylinder block and a second control link end rotatably connected to a second lower link end side of the lower link through a second connecting pin. When viewed in an axial direction of the crankshaft, the second connecting pin is arranged to swing along a lateral direction substantially perpendicular to a center axis of a cylinder of the internal combustion engine.