Abstract: A mining design method for an upper protective layer in coal seam mining, and provides a mining design method for a near-whole rock upper protective layer. Based on information about engineering geologic conditions of a protective layer mining well and physico-mechanical parameters of a coal-rock mass sample, a protective layer mining thickness M and an interval H between the protective layer and the protected layer are determined by means of numerical analysis such that an expansion deformation rate ? of a protected layer, a failure depth K of a floor plastic zone of a protective layer, and a coal seam gas pressure P meet the Provision in Prevention and Control of Coal and Gas Outburst.

Abstract: A method for deformation control of large-span tunnel in chlorite schist stratum. The method divides the large deformation of large-span tunnel in chlorite schist stratum into five deformation grades according to the surrounding rock conditions of the tunnel. In response to each deformation grade, the deformation control of large-span tunnel is determined so as to ensure the safety and stability of the tunnel support structure and to avoid the clearance intrusion caused by tunnel deformation.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore disposed about the central axis, a rim and a web disposed radially between the bore and the rim. The bore has a fore surface and an aft surface. The aft surface of the bore may include an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and an aft base transition portion radially inward of the aft ramp portion. The fore surface of the bore may include a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and a fore base transition portion radially inward of the fore ramp portion. The aft ramp portion includes a substantially linear portion and the fore ramp portion includes a substantially linear portion.

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

Abstract: Provided is a rotating body, comprising: an impeller including: a main body portion; a welded surface formed on a back surface of the main body portion; a recessed portion, which is formed in the main body portion on a radially inner side with respect to the welded surface; and a reinforcing portion, which is formed on the main body portion on the radially inner side with respect to the recessed portion; and a shaft including: a welding surface welded to the welded surface; and a projection portion, which is formed on the radially inner side with respect to the welding surface, projects toward the impeller side with respect to the welding surface, and is inserted into the recessed portion, the shaft receiving a distal end of the reinforcing portion inserted thereinto on the radially inner side with respect to the projection portion.

Abstract: A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A power turbine includes a second stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

Abstract: A vane cluster for a gas turbine engine including an inner diameter platform and an outer diameter platform. A plurality of vanes span from the inner diameter platform to the outer diameter platform. An inbound region is defined between a first vane and a second vane of the plurality of vanes. A plenum is defined in the inner diameter platform at the inbound region. The plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath. A feed hole connects the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.

Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Abstract: Airfoils and gas turbine engines having the same, the airfoils including an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body, wherein at least one wall of the cooling cavity is a curved end wall, and an end wall contoured pedestal positioned adjacent the curved end wall. The end wall contoured pedestal has a first portion with a contoured side wall and a parallel side wall, and a second portion with tapering side walls, wherein the contoured side wall faces the curved end wall, the contoured side wall paralleling a contour of the curved end wall and defining a meter section therebetween.

Abstract: A turbomachine blade that includes an airfoil that includes an intrados wall, an extrados wall, a leading edge, a trailing edge, an internal cavity and a plurality of cooling holes made in the walls and leading and trailing edges, each cooling hole connecting the internal cavity to the exterior, one end of each cooling hole opening up into the cavity, the other end of each cooling hole opening to the exterior through an outlet, wherein the cooling holes are distributed in at least one first alignment and a second alignment made in a wall of the airfoil, wherein this outlet of at least one of the cooling holes belonging to at least the second alignment is an oblong shape with its long dimension along the principal direction of said second alignment.

Abstract: A method for manufacturing a number of gas turbine components includes selecting material for manufacturing a number of components, making at least one coupon of the material for testing of material properties, determining at least one required material property, a target value of the property and an acceptable deviation from the target value, testing the at least one determined material property of the coupon, associating each component, which is made of the selected particular material, with the at least one material property of the coupon, comparing the testing result of the property with the required material property, and rejecting components, the associated at least one property of which do not fulfil the acceptable deviation of the required value of the material property.

Abstract: A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.

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 compressor turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A turbocharger includes: a nozzle drive mechanism for driving a plurality of nozzle vanes; and a support ring for holding the nozzle drive mechanism, the support ring having a main body portion having a heat shielding portion facing a turbine impeller in a direction of a rotational axis of the turbine impeller.

Abstract: A fan exit stator assembly of a gas turbine engine may include a radially inward shroud defining a first slot, a radially outward shroud, and a vane. The vane may include a base portion extending through the first slot and a tip portion coupled to the radially outward shroud. The vane may also include a retainer plate disposed radially inward of the radially inward shroud that projects in a circumferential direction from the base portion of the vane. A circumferential plate dimension of the retainer plate in the circumferential direction is greater than a first slot radius in the circumferential direction of the first slot, thus preventing radially outward movement of the vane relative to the radially inward shroud.

Abstract: A stator ring of a flow path, preferably secondary, of a turbomachine, the ring including an inner platform and an outer platform, a plurality of stators extending radially between the two platforms, in which at least one of the two platforms includes a plurality of integrated platforms, each one of the integrated platforms being integral with one of the stators, and the integrated platforms are all of the same shape as one another, and a plurality of attached platforms, each one of the attached platforms being in the form of a part that is assembled and arranged between two integrated platforms, and the attached platforms are also all of the same shape as one another.

Abstract: The invention relates to a tab (5) for a sealing gasket device of a part of an aircraft gas turbine engine. The tab is arranged in respective slots of adjacent sectorized parts of the turbine engine nozzle. This tab has two bulging ends (51a, 51b) joined by a thinner intermediate part (51c) each having a connection with the other (53a, 53b), which can deform into a flat position by bracing the tab, when excess pressure is applied to its intermediate part from one side of the tab.

Abstract: A rotor machine includes a rotor which includes a recessed portion, a stator blade which includes a stator blade body and a shroud, and a fin. The recessed portion includes a recessed portion radial wall surface which extends in a radial direction, and the recessed portion radial wall surface includes a first wall surface which extends radially outward, a second wall surface which extends further radially outward than the first wall surface, and a protrusion surface which protrudes toward an upstream side in the axis direction from the first wall surface. The shroud includes a shroud radial wall surface facing a downstream side in the axis direction of the recessed portion radial wall surface, and a shroud groove portion is formed in the shroud.

Abstract: The present invention provides a generalized frequency conversion system for a steam turbine generator unit. The system comprises at least a steam turbine (T) with an adjustable rotating speed, a water feeding pump (BFP), a generator (G), a speed increasing gearbox (GB), a variable frequency bus (a, c) and an auxiliary machine connected thereto. With a change in load of the unit, parameters of steam entering the steam turbine (T) and an extracted steam amount are correspondingly adjusted (changed), so that the rotating speed of the steam turbine (T) changes correspondingly; and thus the rotating speed of the water feeding pump (BFP) is changed through the speed increasing gearbox (GB) on the one hand, and the frequency of an alternating current outputted by the generator (G) is changed on the other hand. Other types of frequency converters do not need to be additionally provided. The system is simple, reliable, low in cost, and high in efficiency.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.

Abstract: A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.

Abstract: The present disclosure is directed to systems and methods generating power using supercritical CO2 in a Brayton cycle that incorporates a double-wall turboexpander that includes an inner chamber housing the turbine and an outer chamber that includes a thermal attenuator that reduces the outer chamber wall temperature of the turboexpander. An inner chamber wall separates the inner chamber and the outer chamber within the double-wall turboexpander. In supercritical CO2 applications, the double-wall turboexpander operates at elevated temperatures and elevated pressures. By maintaining the thermal attenuator the outer chamber at an elevated pressure, the differential pressure across the inner chamber wall is reduced, requiring less high-temperature alloy material in the construction of the double-wall turboexpander when compared to a conventional turboexpander.

Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include a blade track coupled with a turbine casing with a clip. The system may further include a nozzle guide vane coupled to the turbine casing. A cavity may be formed by an end of the blade track, the clip, and a portion of the nozzle guide vane. A heat shield may be positioned between the clip and the end of the blade track in the cavity such that an edge of the heat shield and the portion of the nozzle guide vane form a gap. The heat shield and the nozzle guide vane may be positioned such that the gap closes in response to the heat shield and the nozzle guide vane thermally expanding.

Abstract: A fluid damping structure is provided that includes an inner and outer annular elements, first and second ring seals, first and second outer annular seals. The inner annular element has an outer radial surface and a plurality of annular grooves disposed in the outer radial surface. The outer annular element has an inner radial surface. A damping chamber is defined by the inner and outer annular elements, and the first and second inner ring seal. A first lateral chamber is disposed on a first axial side of the damping chamber. A second lateral chamber is disposed on a second axial side of the damping chamber. A plurality of fluid passages are disposed in at least one of the inner annular element or the inner ring seals. The fluid damping structure is configurable in an open configuration and a closed configuration.

Abstract: A fluid damping structure is provided that includes an inner annular element, an outer annular element, a first outer seal, a second outer seal, an inner seal, a damping chamber, a supply plenum, a fill port, and a plurality of fluid passages. The plurality of fluid passages is disposed in at least one of the inner annular element or the inner seal. The fluid damping structure is configured such that one or more of the fluid passages is disposed in an open configuration when a local damping fluid pressure within the damping chamber is less than a local damping fluid pressure in an adjacent region of the supply plenum, and the one or more of the fluid passages is disposed in a closed configuration when the local damping fluid pressure within the damping chamber is greater than the local damping fluid pressure in the adjacent region of the supply plenum.

Abstract: A turbocharger, with a turbine for expanding a first medium that includes a turbine rotor and a turbine housing, a compressor for compressing a second medium that includes a compressor rotor coupled to the turbine rotor via a shaft and a compressor housing, a bearing housing in which the shaft is mounted, a bearing housing cap delimiting the bearing housing facing the turbine, and a turbine cover delimiting the turbine on a side facing the bearing housing and has a section projecting into a recess of the bearing housing cap. On a section of the bearing housing cap delimiting the recess of the bearing housing cap on the outside, which on the outside follows the section of the turbine cover projecting into the recess of the bearing housing cap, an oil trapping lip is formed on a side of the bearing housing cap facing the turbine rotor.

Abstract: A bush having a neck portion (33) for inserting into an aperture of one or both of two components to be fastened together, a radially extending shoulder portion (34) having a rear face (34a) adjacent the neck portion (33) an opposite front face (34b) and a radially outer face (34c) extending between the rear face (34a) and the front face (34b), one or more ventilation slots (36) provided in the rear face extending from a junction between the rear face (34a) and the neck portion (33) whereby, in use, to provide an escape route for air caught between the bush and a component.

Abstract: A turbocharger, with a turbine a compressor, and a turbine and a compressor housing connected with a bearing housing. An inflow housing of the turbine housing and the bearing housing are connected via a fastening device such that the fastening device is mounted to a flange of the inflow housing with a first section and a second section overlaps a flange of the bearing housing at least in sections. Between the first section of the fastening device and nuts of the fasteners, resiliently deformable elements are positioned, which provide a preloading force and compensate for preload losses.

Abstract: A turbocharger, with a turbine and compressor housing connected to a bearing housing. An inflow housing of the turbine and bearing housing are connected via a fastening device mounted to a flange of the inflow housing with a first section and partially overlaps a flange of the bearing housing with a second section. Between the inflow housing and the bearing housing, flanges of a nozzle ring and of a sealing cover are clamped. Adjoining surfaces contacting one another in a region of a first, second, and/or a third contact clamping region are hardened.

Abstract: A gas turbine casing made of composite material, the casing presenting an axisymmetric shape and including, in an axial direction: an upstream flange; a retention zone presenting thickness greater than the remainder of the casing; and a downstream flange. The casing presents, in section on a plane defined by the axial direction and by a radial direction, a profile including at least first and second inclined portions that are inclined relative to each other and relative to the axis of the casing. The first and second inclined portions meet at a point situated between the retention zone and one of the flanges, this point corresponding to the vertex of an angle formed by the first and second inclined portions. The distance between the vertex of the angle and the mean radius of the casing lies in the range 1.5% and 4% of the mean radius of the casing.

Abstract: A casing of a turbocharger, which surrounds the turbocharger radially and axially outside at least in sections. The casing has multiple casing modules including a temperature casing module that surrounds the turbine, the compressor, and/or the bearing housing radially outside and axially outside at least in sections, an inner burst protection casing module following the temperature casing module on the outside, and at least one outer burst protection casing module following the inner burst protection casing module on the outside, which surrounds the inner burst protection casing module.

Abstract: Various embodiments include apparatuses for performing maintenance on a gas turbine bearing area, along with related methods. One apparatus can include: a set of rails sized to couple with the gas turbine and rest coaxially with a bearing adjacent the gas turbine, the set of rails for supporting a portion of a housing of the bearing; a first platform spanning between the set of rails; a lifting device coupled to the first platform for engaging an inlet bellmouth of the gas turbine; and a second platform suspended from the set of rails sized to accommodate an operator.

Abstract: Apparatus and method to wet start the HRSG and combined cycle in the fastest time with minimum thermal stress. This wet start provides the earliest possible cooling steam during acceleration, reducing stress in the superheater, reheater and steam turbine. The gas turbine is started and loaded to full power in the fastest possible time without holds. A once-through HRSG filled with saturated boilerwater including the superheater generates dry steam during acceleration. Start apparatus positions the dryout zone in each superheater tube, controls surge swell, ensures uniform pressure rise, and controls the steam temperature. The superheater generates temperature controlled steam to cool the tubes while heating headers. Superheater and reheater tubes and headers start at saturation and increase to operating with minimum differential temperatures. The superheater evaporating boilerwater supplies constant low temperature dry steam to start the steam turbine without the use of attemporators.

Abstract: A proposed method provides a highly efficient fueled power output augmentation of the liquid air energy storage (LAES) through its integration with the semi-closed CO2 bottoming cycle. It combines the production of liquid air in air liquefier during LAES charge using excessive power from the grid and an effective recovery of stored air for production of on-demand power in the fueled supercharged reciprocating internal combustion engine (ICE) and associated expanders of the power block during LAES discharge. A cold thermal energy of liquid air being re-gasified is recovered for cryogenic capturing most of CO2 emissions from the facility exhaust with following use of the captured CO2 in the semi-closed bottoming cycle, resulting in enhancement of total LAES facility discharge power output and suppressing the thermal NOx formation in the ICE.

Abstract: An oil drain preventing device for a continuously variable valve timing apparatus includes: an advance angle oil passage connected to a continuously variable valve timing (CVVT) journal from an an oil control valve (OCV) groove to which an oil control valve (OCV) is mounted to supply an oil supplied from a hydraulic pump to a continuously variable valve timing (CVVT) apparatus; a retard angle oil passage connected to the CVVT journal from the OCV groove; and a valve unit mounted to the advance angle oil passage and the retard angle oil passage between the oil control valve and the CVVT journal for preventing the oil supplied to the continuously variable valve timing apparatus from being drained by selectively opening/closing the advance angle oil passage and the retard angle oil passage according to a starting ON or a starting OFF of the engine.

Abstract: The present disclosure relates to a sliding cam system for an internal combustion engine. The sliding cam system has a camshaft and a plurality of cam carriers with in each case at least two cams, the plurality of cam carriers being arranged fixedly on the camshaft so as to rotate with it and in an axially displaceable manner. The sliding cam system has a plurality of fluid-actuated actuator apparatuses which are configured in each case for axially displacing a cam carrier of the plurality of cam carriers. The sliding cam system has a fluid feed apparatus which is provided for feeding a fluid in a fluidic connection upstream of the plurality of actuator apparatuses for actuating the plurality of actuator apparatuses. At least two actuator apparatuses of the plurality of actuator apparatuses are coupled fluidically for simultaneous actuation.

Abstract: A multiple variable valve lift apparatus disposed at an intake part and an exhaust part of an engine includes: a moving cam rotating together with a camshaft, being movably disposed in an axial direction of the camshaft, and forming a plurality of cams for realizing valve lift to be different from each other and a cam guide protrusion; an operating unit selectively guiding the cam guide protrusion so as to move the moving cam in an axial direction of the camshaft; a controller controlling an operation of the operating unit; and a valve opening/closing unit opened/closed by contacting any one among the plurality of cams.

Abstract: An actuator for actuating valve-lift modes of a valve train assembly of an internal combustion engine, The valve train assembly is capable of being switched between a first valve-lift mode and a second valve-lift mode. The actuator includes a first body and a second body, The second body is mounted for reciprocal movement with respect to the first body between a first position to cause the first valve-lift mode and a second position to cause the second valve-lift mode. The actuator includes a third body supported by the second body, the third body for moving a first component of the valve train assembly to cause the second valve-lift mode, The third body is moveable relative to the second body. The actuator includes a first biaser for biasing the third body away from the second body towards the first component of the valve train assembly.

Abstract: A multifunctional engine brake, comprising an engine valve motion transformation mechanism, a slow seating mechanism (250), and a timing oil control mechanism. By axially moving a roller (235) on a roller shaft (231), the connections between the roller (235) and different cams (230, 2302) are switched, so as to implement the transformation between different engine valve motions. A roller axial driving mechanism (100) is disposed in the roller shaft (231), thereby achieving a simple and compact structure, a symmetrical and reliable force, and easy manufacturing and assembling. The timing oil control mechanism provides timing oil supply or discharge for the engine brake, thereby eliminating the randomness of the opening or closing of a conventional engine brake, avoiding slipping and impact of the roller during roller translation, and improving the reliability and durability of the brake and engine.

Abstract: An engine is provided with a cylinder head defining a lubrication gallery intersecting a valve guide bore wall, and a valve guide. The valve guide has inner and outer walls intersecting valve-side and port-side ends. The inner wall defines a channel extending from an intermediate region of the guide to the valve-side end. The guide defines a passage extending outwardly from the channel at the intermediate region to the outer wall, with the passage fluidly connected to the gallery. Pressurized lubricant is provided to a lubrication gallery intersecting a valve guide bore wall of the cylinder head. Lubricant is directed from the gallery into a passage extending through an intermediate region of a valve guide. A moving valve stem positioned within the guide is lubricated by flowing lubricant from the passage into a channel intersecting the inner wall of the guide and to a valve end of the guide.

Abstract: A container for containing a liquid within a vehicle, an internal combustion engine comprising a container, a vehicle comprising a container and a method of directing flow of liquid are disclosed. The container comprises an outer wall configured to contain a liquid and a plurality of baffles configured to direct flow of the liquid within the container. The plurality of baffles define a pickup chamber, at least three outer chambers positioned adjacent to the pickup chamber and at least one respective gap for each said outer chamber to allow liquid flow from each outer chamber through the at least one respective gap into the pickup chamber. A directing means is configured to cause liquid flowing from each of the outer chambers to flow around a vertical axis within the pickup chamber.

Abstract: An oil sump, an internal combustion engine, a vehicle and a method are disclosed. The oil sump comprises a container defining a volume for containing oil in which the volume comprises a primary volume for containing an oil outlet, a secondary volume and an intermediate volume. A first wall divides the primary volume from the intermediate volume. The first wall comprises a first restricted flow means configured to enable a restricted flow of oil from the intermediate volume to the primary volume. A second wall comprising a second restricted flow means is arranged to divide the secondary volume from the intermediate volume. A top-up arrangement is configured to direct returned oil to the secondary volume and enable excess returned oil to overflow into the intermediate volume. A first weir means is positioned to enable an overflow of returned oil into the primary volume.

Abstract: When an internal combustion engine is driven at a low rate below a certain threshold value, exemplary embodiments as disclosed herein allow and restrict a reductant flow to an injector in repeating allowing cycles and restricting cycles. During the allowing cycles the controller is set to keep the reductant flow as close as possible a determined low point setpoint value. During the restricted cycles the reductant flow is prevented.