Abstract: A friction bolt assembly to frictionally engage a bore formed in rock strata. The assembly includes an elongate tube and an expander mechanism acted on by an anchor mechanism via an elongate bar or cable. A retainer mechanism is mounted to act between the bar or cable and the tube to prevent ejection of the bar or cable from the assembly should the bar or cable break.

Abstract: A mine safety system is provided for preventing coal dust explosions in an underground coal mine. The system comprises a reservoir, for storing an inerting agent; a compressor, for providing compressed air; and a mixer, coupled to the reservoir and the compressor, for mixing the inerting agent and compressed air and providing the mixture to the underground coal mine. The reservoir is located outside of the coal mine.

Abstract: An internal combustion engine according to the invention comprises at least two engine blocks which are coupled to one another and each of which includes at least two cylinders, each cylinder being connected to a common drive shaft via a transmission and a clutch. If there is a problem with one engine block, same can be disconnected from the drive shaft so that the engine can continue to operate by means of the other engine block.

Abstract: A vacuum pump includes a housing defining a cavity having an inlet and an outlet; a vane member for a rotary driven movement inside the cavity; a drivable rotor inside the cavity; and a rotatable central shaft extending to the cavity. The vane member is slidably arranged in the rotor. The rotor is rotatable together with the vane member. The central shaft comprises a crank pin configured to engage a respective guiding recess of the rotor for driving the rotor at least along a first predetermined rotational angle.

Abstract: A rotor (100) for a turbomachine is provided, having at least two bladed, detachably interconnected rotor stages (1, 3, 6), a flange (17) of a first rotor stage (1) being attached to a rotor disk (25) of a second, adjacent rotor stage (3) via at least one fastening element (7). The rotor disk (25) has a through bore (11) for connecting the two rotor stages (1, 3) by the fastening element (7); the through bore (11) having a cross section that is larger in the circumferential direction (u) of the rotor disk (25) than in the radial direction (r) thereof.

Abstract: A blade (10) for a turbomachine is provided. In at least one cross section disposed orthogonally to a longitudinal blade axis, an outer surface of the blade forms a curve (?) that runs continuously on the inflow side along an at least approximate ellipse (E) between a first separation point (P1) and a second separation point (P2). On the pressure side 12, the curve (?) has an inflection point W. A distance of the second separation point (P2) from the inflection point W along the curve is at least exactly equal, at least twice as great, at least three times as great, or even at least five times as great as a distance of the second separation point (P2) from the first separation point (P1) along the at least approximate ellipse (E). Also described is a blade ring having at least one blade of this kind, as well as a turbomachine.

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a blade extending between the root and tip and extending between the leading edge and trailing edge. The blade includes a pressure side and a suction side defining a thickness therebetween at each point along the span. The blade defines a first chord reduction on at least one of the leading edge or trailing edge along a first portion of the span. Further, the blade defines a frangible line extending from the first chord reduction at least partially along the chord at a point along the span within the first portion of the span.

Abstract: Mistuned bladed rotors and associated manufacturing methods are disclosed. An exemplary method includes forming two or more blades of the bladed rotor where the two or more blades have substantially identical external aerodynamic surfaces and have different internal configurations causing the two or more blades to have different natural frequencies.

Abstract: A rotor assembly of a gas turbine engine may be spoked and includes a rotor and a shell. The rotor has a rotor disk and a plurality of blades each having a platform attached to the rotor disk and with a first channel defined radially between the platforms and the rotor disk. The shell projects aft of the rotor and includes inner and outer walls with a passage defined therebetween. The passage is in fluid communication with the first channel and, together, form part of a secondary flowpath for cooling of adjacent components. The rotor assembly may further include a structure located radially inward of the rotor disk and shell. The structure defines a supply conduit for flowing air from the passage and into a rotor bore defined at least in part by adjacent rotor disks. The entering air, being pre-heated when flowing through the channel and passage, warms the bore and reduces thermal gradients, thus thermal fatigue, across the rotor disk.

Abstract: A gas turbine blade includes a plurality of guide ribs spaced apart from each other in a movement direction of a cooling fluid in order to guide movement of the cooling fluid flowing along a cooling passage formed in the turbine blade, and an opening formed in each of the guide ribs in order to guide a portion of the cooling fluid to a bottom of the cooling passage between the guide ribs or to side walls adjacent to the bottom.

Abstract: The present invention relates to a structure for cooling a turbomachine's rotor part and a rotor and a turbomachine having the same. The structure for cooling a turbomachine's rotor part includes: a dovetail joint part disposed along an outer circumferential surface of a rotor wheel and having a plurality of mounting grooves in which dovetails of buckets are mounted and cooling slots disposed along the outer circumferential surface of the rotor wheel on the dovetail joint part and having a cooling fluid flowing therethrough.

Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes a first cooling circuit having a first portion and a first tip portion and a second cooling circuit having a second portion and a second tip portion.

Abstract: A turbine blade with a cooling structure includes a root member coupled to a turbine disk; an inlet formed in the root member to introduce cooling air to the turbine blade; an airfoil coupled to the root member, the airfoil having a suction-side surface and a pressure-side surface; and an internal cooling channel disposed between the suction-side and pressure-side surfaces of the airfoil and configured to pass the cooling air throughout the airfoil from the inlet to an ejection hole formed on an upper surface of the airfoil. The turbine blade may be included in a turbine of a gas turbine and is provided to blow air passing through the cooling channel toward a leading edge and an upper surface of the airfoil, thereby reducing heat load and thermal stress applied to the turbine blade and preventing the turbine blade from being damaged by the heat load or thermal stress.

Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.

Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100° F. higher than that of the second material. A gas turbine engine is also disclosed.

Abstract: The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A sacrificial anode layer is applied to at least a portion of the sheath so that the sacrificial anode layer will corrode instead of the airfoil.

Abstract: An air-collecting structure effectively cools a transition piece of a duct assembly in a gas turbine combustor. The structure includes a flow sleeve having a plurality of cooling holes and surrounding the transition piece, the cooling holes formed in a lateral side of the flow sleeve to receive a compressed cooling air and arranged in rows running parallel to each other in a longitudinal direction of the flow sleeve, the rows progressing up the lateral side from a lower row to a higher row; and a plurality of scoops arranged in correspondence with predetermined cooling holes among the plurality of cooling holes and configured to collect an amount of air according to row. Each scoop includes an inlet having a predetermined radius for collecting the compressed cooling air. The radius is constant for the scoops of any one row and increases from the lower row to the higher row.

Abstract: A centrifugal compressor includes an impeller and a casing, the casing includes a scroll part forming a scroll flow passage and a diffuser part forming a diffuser flow passage. The diffuser part includes: a first diffuser portion belonging to a first angular range in a circumferential direction of the impeller; and a second diffuser portion belonging to a second angular range downstream of the first angular range in a flow direction of the scroll flow passage, of the angular range in the circumferential direction of the impeller, the second diffuser portion having an outer radius R2 which is defined along a reference circle centered at a rotational center of the impeller. An outer radius R1 of the first diffuser portion in the first angular range is smaller than the outer radius R2 of the second diffuser portion in the second angular range.

Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately +/?0.049 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.

Abstract: A system may include a transition piece, coupled to a support of the system, to receive combustion products from a combustion chamber. The system may also include a turbine nozzle, coupled to a support of the system, to receive combustion products from the transition piece. Additionally, a web plate disposed at a radial position about a turbine axis between the transition piece and the turbine nozzle may form a first seal between the web plate and the transition piece and form a second seal between the web plate and the turbine nozzle. In addition, the web plate may extend in a circumferential direction about the turbine axis and couple to a support of the system. Further, the web plate may include an inner surface, an outer surface, and an arm extending in a radial direction between the inner surface and the outer surface.

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: Disclosed herein is a structure for multi-stage sealing of a turbine, including: an annular multi-stage sealing part disposed on an inner circumferential surface of a fixed body and having different heights of at least two stages; a barrier unit disposed at a central side of the multi-stage sealing part on the inner circumferential surface of the fixed body; and an annular multi-stage tooth part disposed to face the multi-stage sealing part or the barrier unit over an outer circumferential surface of a rotating body and provided with a plurality of teeth, having a relative height corresponding to different heights of the multi-stage sealing part or the barrier unit at an interval between the fixed body and the rotating body.

Abstract: A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti-movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track.

Abstract: A tip sealing structure for a blade includes a casing having an inner circumferential surface facing the blade; a blocking groove formed in the inner circumferential surface of the casing; and a movable seal provided on a tip of the blade and configured to move in a depth direction of the blocking groove. Since the seal is configured to move into the blocking groove, tighter sealing at the tip of the blade can be accomplished. A seal bracket of the moveable seal encloses a movement space open at one end and includes a seal stop formed at the open end. A brush body including top and bottom crossbars is disposed partially within the seal bracket, such that movement of the moveable seal is limited by the bottom crossbar being stopped by the seal stop. A first brush seal is mounted on the brush body and positioned in the blocking groove.

Abstract: A propulsion system includes a propulsor having a driveshaft, an electric machine coupled to the driveshaft of the propulsor, and a combustion engine having an output shaft. The propulsion system additionally includes a one-way clutch operable with at least one of the driveshaft of the propulsor and the output shaft of the combustion engine. The one-way clutch allows for a differential angular velocity of the driveshaft relative to the output shaft in a first circumferential direction and prevents a differential angular velocity of the driveshaft relative to the output shaft in a second circumferential direction.

Abstract: A hybrid jet engine, including a front cowling having a tubular shape, a rear cowling having a tubular shape and connected to the front cowling, a central core disposed within the front cowling and the rear cowling, a shaft disposed longitudinally within the central core, a plurality of main fan blades disposed at a first end of the shaft at the front cowling, a plurality of auxiliary fan blades disposed at a second end of the shaft at the rear cowling, at least one aerodynamic stabilizer disposed on a surface of the central core to extend therefrom, and at least one Tesla one way valve disposed on the surface of the central core to receive the ram air and to provide the ram air to the plurality of auxiliary fan blades.

Abstract: A turbocharger including a pivoting vane (50) aligned with a volute slot (25) of the housing (10) and located proximal a downstream end (57) of a tongue (15) defining an initial inlet throat area (11) of the housing. When the vane is in its fully closed position (60), inlet exhaust gas is prevented from flowing into the volute slot and, therefore, the turbine wheel, until the inlet exhaust gas passes a downstream end (57) of the vane. The vane effectively extends the inlet throat area to define a revised inlet throat area (12). The A/R ratio of the housing progressively varies as the vane pivots between the fully opened and fully closed positions.

Abstract: The invention relates to a system of vanes with adjustable orientation, also called a system of variable stator vanes, for a low-pressure compressor of an axial turbine engine. The system comprises vanes, each having a vane extending radially in a flow of the turbine engine and a spindle having a cylindrical portion connected to a telescopic actuating lever. The cylindrical portion comprises radially extending slot, and the actuating lever comprises a pivot joint housed in the slot, that is configured to communicate a rotary movement to the vane about its spindle. The invention also proposes a compressor and a turbine engine.

Abstract: A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.

Abstract: A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.

Abstract: A variable turbine and/or compressor geometry for an exhaust gas turbocharger may include an adjusting ring for simultaneously adjusting a plurality of guide vanes. The adjusting ring may be operatively connected to an articulated lever via a first contact surface and to an associated adjusting lever of the plurality of guide vanes via a second contact surface. The adjusting ring may include, at least in a region of the first contact surface, an additional component which is pressed into the adjusting ring and which increases the first contact surface operatively connected with the articulated lever.

Abstract: A valve monitoring apparatus has a system to determine a state of a valve. The system determines a fluid flow first pressure at a first location within a gas turbine engine, and a second pressure of a compressed fluid at a second location within the engine when the valve is in the first position; and compares the first and second pressures to determine the valve state. The system is arranged to command the valve to move from the first position towards a second position; determine the second pressure of the compressed fluid at the second location; compare the pressure at the second location when the valve is in the first position to the pressure at the second location when the valve has been commanded to move towards the second position; and, determine whether the valve has moved from the first position towards the second position when commanded to do so.

Abstract: A braking system for the low pressure spool of a gas turbine engine includes a braking assembly connected to the low pressure spool and reversibly configurable between an actuated state and an unactuated state. The braking assembly in the unactuated state allows rotation of the low pressure spool without interference. The braking assembly in the actuated state applies a force opposing the rotation of the low pressure spool. A method of controlling the speed of rotation of a low pressure spool and a method of controlling the speed of rotation of low and high pressure spools are also discussed.

Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.

Abstract: A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.

Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a forward end, an aft end, a first and second side, an outer surface facing a cooling chamber formed between the body and the turbine casing, and an inner surface facing a hot gas flow path for the turbine system. The turbine shroud may also include at least one collection plenum extending within the body between the forward end and the aft end. Additionally, the turbine shroud may include set of cooling passage(s) extending within the body. Each of the cooling passages of the set of cooling passage(s) may include an inlet portion in fluid communication with the cooling chamber, an outlet portion in fluid communication with the at least one collection plenum, and an intermediate portion fluidly coupling the inlet portion and the outlet portion.

Abstract: A strut shield collar can include: a tubular portion including a tubular inside surface and a tubular outside surface; a flange portion extended from the tubular portion toward an outside of the tubular portion and including a flange inside surface; and a grid type mesh formed on at least one of the tubular inside surface and the flange inside surface, wherein the grid type mesh comprises a groove portion and a rib portion, and the groove portion is thinner than the rib portion.

Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.

Abstract: This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

Abstract: A turbine center frame for a gas turbine having a plurality of first components and a plurality of second components alternately mutually adjacently disposed in circumferential direction and bounding a hot gas-conducting flow channel in radial direction, the first components each having two first overlapping portions, and the second components each having two second overlapping portions. In a transition from a first component to a second component, one of the first overlapping portions and one of the second overlapping portions overlap. A centering element, against which, the first components and the second components are braced along the circumferential direction and in the radial direction, centers the first components and the second components relative to a central axis of the turbine center frame.

Abstract: A frangible strut for a gas turbine engine includes a first end to couple to a first structure of the gas turbine engine, and a second end opposite the first end. The second end is to couple to a second structure of the gas turbine engine. The second end includes an outer portion coaxial with and spaced radially apart from an inner portion. The inner portion is to receive a fastening device to couple the second end to the second structure. The outer portion is coupled to a body of the frangible strut. The inner portion is interconnected to the outer portion by a plurality of frangible members that are spaced apart about a perimeter of the inner portion, and each of the frangible members are configured to release the inner portion from the outer portion. The frangible strut includes the body interconnecting the first end and the second end.

Abstract: An efficiency evaluation method of an RCAES system is disclosed, and the method includes calculating electric energy charged by an electric power system in a compression process, calculating electric energy discharged to the electric power system in an expansion process, and calculating a ratio of the electric energy discharged in the expansion process to that charged in the compression process, and taking the ratio as an efficiency of the whole RCAES system; wherein gas in operation is ideal gas, air mass flow rates in the compression and expansion processes are known and constant in operation, an isothermal model is adopted for the CASV of which the temperature is the same with ambient circumstances, and the temperature and pressure of compressed air after throttling become constant. A corresponding system is also disclosed.

Abstract: Provided is an opposed-piston engine which attains high output, ensures combustion toughness, and includes a simplified configuration of a crankshaft counter-rotation synchronization mechanism which rotates crankshafts in engine units in opposite directions. An opposed-piston engine 10 of the present invention includes a first engine unit 11 and a second engine unit 21. The first engine unit 11 and the second engine unit 21 respectively include a first cylinder 12 and a second cylinder 22 independent of each other. In addition, a first valve driving mechanism 19 and a second valve driving mechanism 20 which control valves also function as a crankshaft counter-rotation synchronization mechanism 29 which rotates a first crankshaft 14 of the first engine unit 11 and a second crankshaft 24 of the second engine unit 21 in the opposite directions.

Abstract: A four-stroke internal combustion engine is disclosed. A camshaft and a crankshaft if the engine are synchronized to rotate at a same rotational speed. A first linkage arrangement is configured to change the motion of an exhaust valve head. A second linkage arrangement is configured to change the motion of the intake valve head. A control unit is configured for controlling the first linkage arrangement to selectively prevent the motion of the exhaust valve head and for controlling the second linkage arrangement to selectively prevent the motion of the intake valve head.

Abstract: A four-stroke internal combustion engine is disclosed. A camshaft and a crankshaft if the engine are synchronised to rotate at a same rotational speed. A first linkage arrangement is configured to change the motion of an exhaust valve head. A second linkage arrangement is configured to change the motion of the intake valve head. A control unit is configured for controlling the first linkage arrangement to selectively prevent or reduce the motion of the exhaust valve head and for controlling the second linkage arrangement to selectively prevent or reduce the motion of the intake valve head.

Abstract: This disclosure relates to a roller tappet, in particular for a high-pressure fuel pump. The roller tappet is guided in a direction of a longitudinal axis thereof in a housing receptacle and is driven in the longitudinal direction by cams of a camshaft. The roller tappet has a tappet body. The tappet body has a tappet skirt, a pump piston contact seat, and a rotatably mounted roller, by means of which the roller tappet is supported on the camshaft. The tappet body has a guide cylinder, which is mounted in the housing receptacle and on which the roller is mounted, and a cup-shaped sleeve having the pump piston contact point, which cup-shaped sleeve is supported axially and radially in the guide cylinder.

Abstract: An internal combustion engine valve timing control device includes a communication passage formed in a first rotating member to communicate with a working chamber, and including a first opening. The first opening is opened to a back pressure chamber when a tip portion of a lock member is inserted in a lock hole, and is closed by the lock member when the tip portion of the lock member is out of the lock hole. A first cross-sectional area is smaller than a second cross-sectional area, wherein the first cross-sectional area is a smaller one of a minimum cross-sectional area of the communication passage and an open cross-sectional area of the first opening, and the second cross-sectional area is a smaller one of a minimum cross-sectional area of an exhaust passage and an open cross-sectional area of an opening of the exhaust passage opened to the back pressure chamber.

Abstract: An actuator arrangement for controlling a latching arrangement of a dual body rocker arm of an internal combustion engine, the dual body rocker arm comprising a first body, a second body, and the latching arrangement, the latching arrangement being controllable to latch and unlatch the first body and the second body. The actuator arrangement includes: an actuation source; a shaft including a cam for controlling the latching arrangement; and a gear mechanism for translating a continuous rotation of the actuation source into an intermittent rotation of the shaft in steps of a predefined degree. In use, a continuous rotation of the actuation source causes, via the gear mechanism, the shaft to rotate in steps of a predefined degree, thereby to change an orientation of the cam relative to the latching arrangement by a predefined amount, so as to control the latching arrangement.

Abstract: An engine is provided which includes an oil gallery, a base attaching seat in an engine frame wall, and a base for component mounting attached to the base attaching seat. An oil cooler and an oil filter are mounted on the base for component mounting, and the base attaching seat is provided with an oil inlet communicating with an upstream-side passage of the oil gallery, and an oil outlet communicating with a downstream-side passage of the oil gallery. Attaching the base for component mounting to the base attaching seat allows engine oil flowing into the oil inlet of the base attaching seat from the upstream-side passage of the oil gallery to pass the base for component mounting, the oil cooler, and the oil filter, and flow out of the oil outlet of the base attaching seat to the downstream-side passage of the oil gallery.

Abstract: A fluid management system, or flow control system, for an automotive propulsion system is provided. The system includes a housing defining a sump configured to collect a volume of liquid and gaseous fluid and a pump configured to pump fluid from the sump. The pump defines a pump inlet and a pump outlet. A conduit is in fluid communication with the pump outlet. A passive valve is disposed within the conduit, the conduit defining a conduit outlet downstream of the passive valve, and the conduit further defining an orifice between the pump and the passive valve. The passive valve allows hydraulic fluid to flow past the valve, while substantially preventing air from flowing past the passive valve. The air is instead bled out through the orifice, along with some of the hydraulic fluid.