Abstract: A method for finishing a film cooled article includes providing a film cooled article including at least one inner cooling plenum and at least one opening connecting the inner cooling plenum to an exterior surface of the film cooled article, positioning a machining element in contact with the exterior surface of the film cooled article, automatically moving the machining element along the exterior surface while maintaining contact between the machining tool and the surface, identifying an actual position of at least one film opening based on sensory feedback from the machining element using a controller, removing material from the exterior surface at the at least one film opening using the machining element, thereby creating a depression at the at least one film opening.

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.

Abstract: A rotor blade for a gas turbine that is configured for use within a row of samely configured rotor blades attached to and circumferentially spaced about a rotor disc. The rotor blade may further include: an airfoil defined between pressure and suction faces; and a midspan shroud comprising a pressure wing and a suction wing extending from the airfoil. The pressure wing and the suction wing of the midspan shroud may be configured so to cooperatively form an interface between installed neighboring ones of the rotor blades within the row of samely configured rotor blades. The interface may include a first one of the pressure wing and the suction wing disposed as an upstream wing and a remaining other one of the pressure wing and the suction wing disposed as a downstream wing. The interface may include the upstream wing and the downstream wing configured as a downstream narrowing step.

Abstract: A system includes a turbomachine blade segment including an airfoil with an exterior surface, and a platform coupled to the airfoil having a first side and a second side. The system also includes a concave fillet transition extending between the airfoil and the platform. The concave fillet transition includes one or more interface ply segments extending across the exterior surface of the airfoil and the first or the second side of the platform to form a continuous surface between the airfoil and the platform.

Abstract: A rotor disk blade for a turbine engine, the blade being made of composite material including fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a portion constituting an airfoil and a blade root forming a single piece, the blade root having two substantially plane opposite lateral flanks that are formed respectively extending the pressure side surface and the suction side surface of the airfoil. The blade root is clamped between two metal plates fastened against the lateral flanks of the blade root by a bolt and a nut passing through the plates and the blade root. The bolt has a head bearing against one of the two plates. The nut has a head bearing against the other plate.

Abstract: It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.

Abstract: An arrangement for securing a functional position of a shroud plate of a rotor of a gas turbine, which shroud plate is arranged on an outer circumference of a rotor disc of the rotor, relative to a moving blade of the rotor arranged on the outer circumference of the rotor disc, wherein a channel portion of an annular cooling channel of the rotor is formed between the shroud plate located in its functional position and a side, facing the shroud plate, of a blade root of the moving blade. A rotor assembly for a rotor of a gas turbine, having a rotor disc, a moving blade ring arranged on the outer circumference of the rotor disc and a shroud plate ring arranged on the outer circumference of the rotor disc.

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

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: A method of fabricating airfoil cluster includes providing an airfoil cluster that has a pair of spaced-apart airfoils that extend from a common platform wall. The airfoil cluster is then divided through the common platform wall to provide separate first and second airfoil segments. At least one cooling hole is then formed in at least one of the first and second airfoil segments. The segments are then metallurgically fused together in a distinct metallurgical joint in the common platform wall.

Abstract: A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided.

Abstract: To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.

Abstract: An alignment tool for use in a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clamp portion, a component engagement portion and an arm portion that extends between the clamp portion and the component engagement portion. The clamp portion establishes a fixed datum surface for positioning a component within the gas turbine engine.

Abstract: The invention relates to a mold for injecting a layer of abradable material, such as silicone, inside an inner shroud of an axial-flow turbomachine. The mold comprises a circular wall or tubular wall extending axially and two annular walls extending radially outwardly from the axial ends of the axial wall. Each radial wall of the mold comprises an annular hook in contact with the outer surface of the shroud so as to hold the mold against the shroud. The injection pressure presses the hooks against the shroud, providing a seal. The walls form an annular molding cavity inside the inner shroud in combination with the inner shroud. The invention also relates to a method for molding an abradable layer inside the shroud with the aid of the mold. The latter is deformed by spreading apart the hooks so as to fit over the shroud.

Abstract: A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.

Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.

Abstract: A method of working a brush seal assembly for a turbine engine is disclosed and includes the steps of removing an alignment tab from a used brush seal assembly, restoring at least one dimension of the alignment tab to a desired condition and attaching the restored alignment tab to a new brush seal assembly.

Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls, with the radially-extending sidewalls and the radially inner surface defining a pocket. A rail shield has radially-extending walls that line the radially-extending sidewalls. A spring is configured to bias the rail shield radially inward.

Abstract: A gas turbine engine assembly comprising a rotor, a gas path component, and a carrier. The rotor includes a shaft adapted to rotate about an axis and a gas-path component that extends from the shaft for rotation therewith about the axis. The carrier extends around the gas-path component to block gasses from passing over the gas-path component during rotation of the rotor.

Abstract: In one aspect the present subject matter is directed to a system for supporting a turbine shroud. The system includes a shroud support at least partially defining a first piston sleeve and a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head. The first piston head is slideably engaged with an inner surface of the first piston sleeve. The second piston head is slideably engaged with an inner surface of a second piston sleeve. The system also includes a turbine shroud that is fixedly connected to the piston assembly and that extends radially inwardly from the shroud support. The piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a change in a radial force applied to a hot side surface of the turbine shroud.

Abstract: A clearance control assembly for a gas turbine engine includes a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly.

Abstract: The present application relates to an axial turbomachine gaseous flow-guiding element, such as a compressor inner shroud or vane. The element includes a plasma generator including: a layer of dielectric material with a guiding surface in contact with the gaseous flow, a first electrode placed in the guiding surface, and a second electrode electrically isolated from the first electrode by means of the dielectric layer. The plasma generator drives the gaseous flow along the guiding surface from the first electrode to the second electrode and includes a third electrode covered by the dielectric layer and electrically connected to the second electrode, so as to participate in the generation of the plasma in combination with the first electrode and the second electrode, the second electrode being closer to the guiding surface than the third electrode.

Abstract: A variable vane control system for controlling the angle of rotation of a circumferential row of variable vanes of a gas turbine engine. The control system includes a mechanical linkage operable to rotate the variable vanes, one or more actuators for operating the linkage and one or more position sensors for detecting the respective actuation positions of the one or more actuators. The control system further includes a linkage position signalling switch for signalling that the mechanical linkage is at a calibration position corresponding to a predetermined rotation angle of the vanes. The control system further includes a controller for controlling the one or more actuators and thereby controlling the angle of rotation of the vanes, based on the detected actuation positions which the controller correlates with vane rotation angle.

Abstract: An improvement to a turbocharger having a housing (10) with a slot (25) located along a mid-line of the housing (10) above the turbine wheel (29) and a tongue (15) defining the end of an initial inlet throat area (11) of the housing (10), the slot (25) permitting inlet exhaust gas which flows past the tongue (15) to flow into the turbine wheel (29), the improvement being a pivoting vane (50) aligned with the slot (25) and having an upstream end (55) located at a downstream end (57) of the tongue (15). When the vane (50) is in its fully closed position (60), the inlet exhaust gas is prevented from flowing into the slot (25) and, therefore, the turbine wheel (29), until the inlet exhaust gas passes the downstream end (57) of the vane (50). The vane (50) effectively extends the tongue (15) to define a revised inlet throat area (12). The A/R ratio of the housing (10) progressively varies as the vane (50) pivots between the fully opened (70) and fully closed (60) positions.

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.

Abstract: A method of determining a faulty sensor of a sensor array of a gas turbine engine, the sensor array including at least first, second and third sensors, the method including the steps of: measuring a first set of sensor outputs prior to engine startup from each sensor, and calculating a first difference in the measured value for each sensor pair; after a period of time, measuring a second set of sensor outputs prior to engine startup from each sensor, and calculating a second difference in measured value for each sensor pair; calculating a further difference between the calculated first and second differences for each sensor pair; and identifying a failed sensor where two or more sensor pairs including a common sensor have a further difference above a predetermined threshold.

Abstract: A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling flow inserts direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.

Abstract: Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web.

Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.

Abstract: A support apparatus for disassembling and assembling a gas turbine engine includes an exhaust nozzle attaching and detaching device for guiding movement of an exhaust nozzle in an axis direction and including: a first guide jig detachably fixed to a casing; and a first holding tool detachably supporting the nozzle and engaged with the first guide jig, thereby enabling attaching and detaching the nozzle easily and securely while leaving the engine in a horizontal attitude. The apparatus also includes a low-pressure turbine attaching and detaching device guiding movement of a low-pressure turbine in the axis direction and including: a second guide jig detachably fixed to the casing; and a second holding tool detachably supporting the turbine and engaged with the second guide jig, thereby enabling attaching and detaching the turbine easily and securely while leaving the engine in the horizontal attitude.

Abstract: The invention relates to a thermal to energy conversion method and system using a Rankine cycle equipped with a heat pump, wherein heat pump (2) is integrated in the Rankine cycle.

Abstract: A method for converting heat from a heat source to mechanical energy is provided. The method comprises heating a working fluid E-1,3,3,3-tetrafluoropropene and at least one compound selected from 1,1,1,2-tetrafluoroethane and 1,1,2,2-tetrafluoroethane using heat supplied from the heat source; and expanding the heated working fluid to lower the pressure of the working fluid and generate mechanical energy as the pressure of the working fluid is lowered. Additionally, a power cycle apparatus containing a working fluid to convert heat to mechanical energy is provided. The apparatus contains a working fluid comprising E-1,3,3,3-tetrafluoropropene and at least one compound selected from 1,1,1,2-tetrafluoroethane and 1,1,2,2-tetrafluoroethane. A working fluid is provided comprising an azeotropic or azeotrope-like combination of E-1,3,3,3-tetrafluoropropene, 1,1,2,2-tetrafluoroethane and 1,1,2,2-tetrafluoroethane.

Abstract: A thermodynamic system and method for performing work includes a working fluid and a fluid pump for pumping the working fluid through a cycle. A thermal input supplies heat to the working fluid. An expansion device downstream of the thermal input converts at least the heat of the working fluid to useful work. A heat exchanger downstream of the expansion device has a first portion to transfer heat from downstream said expansion device to a second portion at or upstream of said thermal input. A conversion device expands the working fluid with constant enthalpy from a higher to a lower pressure.

Abstract: An adjustable camshaft can be used in valve drives of internal combustion engines, amongst other places. The adjustable camshaft may include an outer shaft and an inner shaft that is concentric with and rotatably supported in the outer shaft. A cam having a cam bore may be rotatably supported on an outer surface of the outer shaft so as to form a slide bearing gap between the cam and the outer shaft. The cam may be rotatably-fixed to the inner shaft so that the inner shaft and the cam rotate with one another. Furthermore, the adjustable camshaft may include an oil channeling groove disposed beneath the cam in the outer surface of the outer shaft. In many cases, at least one side of the oil channeling groove may be exposed such that it extends beyond the slide bearing gap and the cam.

Abstract: An internal combustion engine optimizing small-size arrangement of the valve drive mechanism, considering that the exhaust valve diameter is smaller than the intake valve diameter. Intake and exhaust valves are in a radial arrangement, intake and exhaust cam surfaces are inclined relative to intake and exhaust cam axes, intake and exhaust rocker arm support members are inclined correspondingly in the same way and disposed between an intake camshaft and an exhaust camshaft. Pivotal support base portions of intake rocker arms and pivotal support base portions of exhaust rocker arms are disposed such that the distances thereof from a joining surface joining a cylinder head and a cylinder body are different.

Abstract: A rocker arm assembly includes an outer arm having a first outer side arm and a second outer side arm, each of the first and second outer side arms having a low lift lobe contacting surface, an inner arm having a high lift lobe contacting surface and disposed between the first and second outer side arms, the inner arm having a first end and a second end operably associated with a lash adjuster and defining a latch bore, and a latch assembly arranged at least partially within the latch bore. The latch assembly is movable between a first configuration and a second configuration. In the first configuration, the latch assembly engages the outer arm such that the outer arm rotates with the inner arm, and in the second configuration, the latch assembly disengages the outer arm such that the outer arm rotates independently from the inner arm.

Abstract: An adjusting device for adjusting valve clearance of a charge-cycle valve of an internal combustion machine is provided. The adjusting device includes a pivoted rocker lever, at one end of which an actuation element is positioned configured to transfer a force to the charge-cycle valve. A transmission element is attached to the actuation element at an opposite end to the charge-cycle valve of which a sleeve area is positioned, which is used to support the transmission element regarding the actuation element. A method for adjusting valve clearance of a charge-cycle valve of an internal combustion machine using an adjusting device is also provided.

Abstract: A rocker arm for an engine valve actuator assembly is disclosed. The rocker arm may include a rocker arm body disposed between a first and second arm end. Furthermore, a rocker arm bore and an adjuster compartment may be defined proximal to the second arm end. The rocker arm may further include a roller positioned at the first arm end and operably coupled to a cam, the cam configured to actuate the rocker arm between a first and second position. The rocker arm may further include a shaft inserted through a shaft mounting aperture and the rocker arm is configured to rotate about the shaft between the first and second positions. Furthermore, a fluid passage may be defined within the rocker arm body extending between a first passage opening formed in a bearing surface of the shaft mounting aperture and a second passage opening that opens into the adjuster compartment.

Abstract: The variable valve actuating device (20) comprises a valve lifter (24) interposed between a swing end of a rocker arm 22 and a stem end of an engine valve (17), and a switch pin (53) slidably received in the valve lifter (24) so as to selectively abut the end surface of the valve stem as the valve lifter is actuated by a cam (21a). The swing end of the rocker arm abuts an upper end of a projection (55) projecting from the upper end of the valve lifter via an engagement feature (26b, 55a) that prevents a rotational movement of the valve lifter relative to the swing end around the axial line of the valve stem.

Abstract: An engine roller lifter for use in a valve train of an internal combustion engine and constructed in accordance to another example of the present disclosure includes a body having an outer peripheral surface configured for sliding movement in a bore provided in the engine. The bore is supplied by an oil passage communicating therewith. The body can define a transverse passage. A groove can be formed around the body and inset from the outer peripheral surface. A connecting channel can be formed in the body and inset from the outer peripheral surface, the connecting channel fluidly connects the groove and the transverse passage. A roller bearing can be rotatably mounted to the body and configured for rolling contact with an engine camshaft. Oil received at the groove from the bore flows along the connecting channel, into the transverse passage and onto the roller bearing.

Abstract: A continuous variable valve duration apparatus may include: a camshaft; first and second cam portions on which a cam is formed respectively, the camshaft being inserted into the first and second cam portions such that relative phase angles with respect to the camshaft are variable; first and second inner brackets transmitting rotation of the camshaft to the first and second cam portions respectively; a slider housing in which the first and the second inner brackets are rotatably inserted; first and second guiding portions formed on the slider housing; a cam cap on which a cam cap guide contacting the second guiding portion is formed; a control shaft parallel to the camshaft; a control rod eccentrically formed on the control shaft; a guide head on which a head guiding portion and a head hole are formed; and a control portion selectively rotating the control shaft.

Abstract: A camshaft phaser, including: a stator to receive rotational torque from an engine and including a radially inwardly facing surface and a slot in the radially inwardly facing surface; a rotor to non-rotatably connect to a camshaft, to be connected to an electric motor and including a first radially outwardly extending protrusion; and a spring non-rotatably connected to the stator and including a first portion disposed in the slot. The electric motor is arranged to rotate the rotor with respect to the stator. In a first circumferential position of the rotor with respect to the stator: no portion of the spring is disposed in the indent; and a second portion of the spring extends radially inwardly past the radially inwardly facing surface. In a second circumferential position of the rotor with respect to the stator, the second portion of the spring is disposed in the indent.

Abstract: The invention relates to a rotor for a camshaft adjuster for rotation about a rotation axis. The rotor has an inner sheath and an outer sheath and at least one control vane, pointing at least substantially radially away from the rotation axis, having a first control vane side and a second control vane side. The rotor furthermore has a first liquid channel system and a second liquid channel system, wherein the first liquid channel system opens in a first liquid channel opening and the second liquid channel system opens in a second liquid channel opening. The rotor comprises: a first sintered joining part, a second sintered joining part which is joined to the first sintered joining part and an insert part which is inserted in an intermediate chamber which is formed by at least one of a first recess of the first sintered joining part and a second recess of the second sintered joining part. The invention further relates to a parts set and to a method for producing a joined component.

Abstract: A cam phaser including a rotor; and a stator, wherein the rotor is rotatable relative to the stator, wherein a lobe of the rotor is arrangeable between two bars of the stator, wherein the lobe divides an intermediary space formed between the two bars into a first pressure cavity and a second pressure cavity, wherein a locking device including a spring loaded locking bolt and a locking disc is configured to lock the stator relative to the rotor in an end position, wherein the locking provides a locking clearance for moving the rotor relative to the stator, wherein the locking disc includes a contact element for adjusting the end position.

Abstract: A valve opening and closing timing control apparatus includes: a driving side rotor synchronously rotating with a crankshaft of an engine; a driven side rotor disposed coaxially with the driving side rotor and synchronously rotating with a camshaft in the internal combustion engine; a fluid pressure chamber formed on at least one of the driving side and driven side rotors, and partitioned into advance angle and retard angle chambers; a bolt disposed coaxially with a rotary axis of the driven side rotor, connecting the driven side rotor and the camshaft, and including a cylindrical portion coaxial with the rotary axis; and a partition body including a press-fit portion press-fitted into the cylindrical portion, and partitioning the cylindrical portion into first and second flow passages for use for feeding and discharging working fluid to and from the fluid pressure chamber, wherein the press-fit portion is provided with a cutting portion.

Abstract: A valve device for an internal combustion engine (1) includes a camshaft (16), a cam (17), a control shaft (15), an input arm (14), a first rocker arm (13a), a second rocker arm (13b), a first valve (603a), a second valve (603b), and a slider (18). The input arm (14) is configured such that a cam torque of the cam (17) is transmitted thereto. The slider (18) is configured to allow the input arm (14) to be supported by the control shaft (15). The slider (18) is configured to support the first rocker arm (13a) in a power transmittable manner such that the cam torque transmitted to the input arm (14) is transmitted to the first rocker arm (13a). The slider (18) includes a torsion portion (23) configured to connect the first rocker arm (13a) with the second rocker arm (13b) such that the cam torque transmitted to the first rocker arm (13a) is transmitted to the second rocker arm (13b) via the torsion portion (23).

Abstract: There is provided an engine lubricating device with which passage resistance of an oil strainer can be reduced and a support stay for an oil filter is unnecessary. An oil strainer includes an outer cylinder and an inner cylinder, the outer cylinder and the inner cylinder respectively have straight central axes and form inner and outer double cylinders, the outer cylinder has a strainer inlet at a lower end, the inner cylinder has a peripheral wall formed as a filter portion, the oil strainer is led out in an orientation inclined downward from the cylinder block toward an inner bottom portion of an oil pan, an upper end portion of the outer cylinder is fixed to a cylinder block, and an upper end opening portion of the inner cylinder communicates with an oil passage inlet of the cylinder block.

Abstract: A housing of a compressor for an internal combustion engine is provided. The housing includes a first air inlet portion. Further, housing includes a tubular wall defining an annular chamber along a circumference of the first air inlet portion. Tubular wall comprising a second air inlet portion. Housing further includes an opening formed in a wall of first air inlet portion, contiguously extending along the circumference of the first air inlet portion, to fluidly couple the annular chamber with the first air inlet portion. The opening being formed at an offset from the second air inlet portion. The opening defines a first edge and a second edge in the wall of the first air inlet portion. The first edge and the second edge are radially offset from each other with respect to a central axis of the first air inlet portion.