Abstract: A bipartite sensor array comprising two portions capable of assembly into a single sensory system. A first portion includes rigid bodies connected by elongate flexures and fitted with gravimetric tilt sensors. The elongate flexures are capable of non-monotonic and non-constant bend in two degrees of freedom. A second portion includes rigid bodies connected by joints, contains the first portion. The second portion, which may be delivered and assembled separately from the first, provides rigidity and protection, enabling the first portion to have short rigid bodies and long connecting flexures, thereby reducing the number of sensors required. The bipartite sensor array is applicable to geotechnical measurements of soil and civil structures.

Abstract: A running tool for deploying a tubular string into a wellbore and methods for operating a wellbrore using the running tool are disclosed. The running tool includes a tubular body and a latch for releasably connecting the tubular string to the body. The running tool further includes a lock to keep the latch engaged.

Abstract: A system and method of transmitting measurement-while-drilling (MWD) data while drilling a wellbore in a subterranean formation are provided. The system utilizes a transmission sub located uphole of the drill bit which transmits an electromagnetic signal through the surrounding drilling fluid to a receiver assembly located farther uphole at a position suitable for relaying the signal to the surface.

Abstract: A method for determining along relatively uniformly spaced apart parallel first and second wellbores situated in an underground hydrocarbon-containing formation, regions within the formation, including in particular regions between such wellbores, to inject a fluid at a pressure above formation dilation pressure, to stimulate production of oil into the second of the two wellbores, and subsequently injecting fluid at pressures above formation dilation pressures at the discrete regions along such wellbores determined to be in need. An initial information-gathering procedure is conducted, wherein fluid is supplied under a pressure less than formation dilation or fracture pressure, to discrete intervals along a first wellbore, and sensors in the second wellbore measure and data is recorded regarding the ease of penetration of such fluid into the various regions of the formation intermediate the two wellbores.

Abstract: A tool insertable into a wellbore for sampling formation fluids includes a body, and sample probe assemblies that project radially outward from the body and into sampling contact with the wellbore wall. Packers are provided on the outer terminal ends of the sample probe assemblies and which are urged against the wellbore wall. Actuator driven linkage assemblies selectively deploy and retract the packers from and back into the body. The sample probe assemblies are disposed at substantially the same axial location on the body, and are angularly spaced about an axis of the body. Each sample probe assembly is independently actuated, so that a discrete azimuthal portion can be sampled, and each has a dedicated sample container for storing sampled formation fluid.

Abstract: A radial piston motor comprises cylinder-piston units arranged in a star shape, a housing, an output shaft, an inner axial housing collar, an outer axial shaft collar, an output flange, an output shaft, and a brake positioned at least in certain sections between the inner axial housing collar and the outer axial shaft collar. The output flange is attached to the output shaft. The output flange is attached to the shaft collar radially outside the shaft collar.

Abstract: A method, including: replacing an original blade shelf (16) of a gas turbine engine blade (10) with a new blade shelf (64) that is located closer to a base (18) of the blade than the original blade shelf; adding mass to the blade until a mass of the blade with the new blade shelf is greater than a mass of the blade with the original blade shelf in order to maintain a same contribution by the blade with the new blade shelf as a contribution by the blade with the original blade shelf to a dynamic balance of a rotor arrangement.

Abstract: The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.

Abstract: A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.

Abstract: The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.

Abstract: An object is to provide a radial turbine blade that can reduce an impact loss of inflowing gas at a leading edge of the turbine blade and achieve a higher turbine efficiency, even in a case of a flow field corresponding to a low turbine operational velocity ratio U/C0 due to a throttling operation on a variable nozzle mechanism of a variable geometry turbocharger. In a radial turbine blade, a hub-side end portion Pa at a leading edge 51 of a turbine blade 50 is formed to be positioned more on a rear side in a rotation direction R of the turbine blade 50 than a shroud-side end portion Sc at the leading edge 51, and a straight line connecting between the shroud-side end portion Sc and the hub-side end portion Pa is inclined with respect to a straight line extending in a rotation axis direction from the shroud-side end portion Sc at the leading edge 51 onto a hub 17 surface by an angle in a range from 30° to 70° as viewed in the radial direction of the turbine blade 50.

Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.

Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

Abstract: The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity, and at least a first impingement device arrangeable within the cavity. The at least first impingement device is self-locking, resilient and preloadable and has at least one locking element to lock the at least first impingement device in place in the cavity via a force fit between the at least one locking element and the inner wall of the cavity wherein the locking element of the at least first impingement device is embodied as a protrusion extending in an assembled state of the at least first impingement device in the cavity basically perpendicular to a surface of a side wall of the at least first impingement device in a direction towards the inner wall.

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane.

Abstract: A platinum plus chromium coating applied to the roots and firtrees of turbine blades where the inclusion of chromium creates a single phase outer zone which minimizes diffusion paths for sulphur which can preferentially diffuse down phase boundaries and enables a chromium rich outer oxide scale to form on top of the coating.

Abstract: A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing.

Abstract: A guide vane assembly for a stator vane stage comprises at least two aerofoil members joined together using a vane assembly attachment web. The vane assembly attachment web may be provided at the inner and/or outer radius of the aerofoil members. The vane assembly attachment web allows the guide vane assembly to be attached to an inner and/or outer attachment ring, thereby forming a stator vane stage. Such an arrangement may allow composite fiber reinforced guide vane assemblies to be readily assembled together to form stator vane stages. Stator vane stages that comprise such composite fiber reinforced guide vane assemblies may be lighter than conventional metallic stator vane stages.

Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

Abstract: A sealing device for a turbine has a sealing member provided in a gap between a rotor and a stator arranged to surround the rotor, and a fluid path provided within the stator, to introduce, into the stator, a cooling medium used to cool stationary blades extending radially inward from the stator, and to flow the cooling medium at least to an upstream side of the sealing member.

Abstract: A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components. The invention furthermore relates to a method for producing such a brush seal system and to a thermal gas turbine having such a brush seal system.

Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.

Abstract: A vane intended to be mounted in a supply fluid pattern, includes a blade delimited in a lateral direction by an outer surface, the blade housing a data routing channel and having a groove leading to the outer surface and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending there through. The data collecting means include one of an inserted tube and a cable, and the groove is formed in one of the outer surface opposite that whereto the inserted tube and the cable leads, and the blade that includes an orifice passing therethrough the outer surface.

Abstract: A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses. The control processor assembly is configured to control the acoustic speaker and laser vibrometer, to decompose the sensed vibration signatures into resonant frequencies of the airfoil, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.

Abstract: A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers may be between the metal rings and composite shell which may be connected by a shrink bonded joint. The metal rings may include a single seal tooth ring with an annular radially extending seal tooth. A method for fabricating the spool may include fabricating one or more metal rings with the features therein, positioning the metal rings in place on an outer surface of an uncured composite spool shell of the spool before curing the shell, and curing the shell with the one or more metal rings positioned in place. Alternatively, rings may be heated to a temperature at least sufficient to slide rings over a cured composite shell, and allowed to cool and shrink onto shell.

Abstract: A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.

Abstract: An oil cooling system is provided. The system may comprise an oil inlet, a manifold fluidly coupled to the oil inlet, and a support strut comprising internal tubing fluidly coupled to the manifold. A heat exchanger may be fluidly coupled to the internal tubing of the support strut. A nose cone may be disposed forward of the heat exchanger and configured to rotate about an axis. The heat exchanger may be radially inward from a portion of the nose cone. A gas turbine engine is also provided. The gas turbine engine may comprise an epicyclic gear system and fan mechanically coupled to the epicyclic gear system. The fan may be configured to rotate about an axis. A nose cone may be coupled to the fan and configured to rotate about the axis. A heat exchanger may be aft of the fan and in fluid communication with the epicyclic gear system.

Abstract: A double frangible bearing support structure supports a low pressure rotor of an aircraft engine. The support structure has a first bearing assembly including a first bearing supported by a first bearing support adapted to buckle or frange when subject to a predetermined critical load resulting from an abnormal rotor imbalance. The support structure has a second bearing assembly comprising a second bearing having rolling elements disposed between inner and outer races. The outer race is connected to a second bearing support by means of frangible bolts adapted to fail when subject to a predetermined critical load resulting from radial displacements and loads of the low pressure rotor following decoupling/franging at the first bearing support.

Abstract: A bearing system and method may include a bearing element that may have a first surface. A mating element may have a second surface that may face the first surface. A fluid film interface may be defined between the first and the second surfaces. The mating element may rotate about an axis and relative to the bearing element. An axial direction may be defined parallel to the axis. A radial direction may be defined perpendicular to the axis. The first surface may have a profile that may vary in the axial direction and that may varies in the radial direction. The profile may direct a fluid present in the fluid film interface in a direction or directions having circumferential and/or axial components.

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

Abstract: Various embodiments include approaches for installing a flow sleeve relative to a gas turbine transition piece. Some embodiments include an apparatus for coupling a gas turbine transition piece with a flow sleeve, the installation apparatus having: a radially inner ring; a plurality of expander segments extending radially outward from the radially inner ring, the plurality of expander segments each having an axially ramped segment sized to gradually expand the flow sleeve to couple with the gas turbine transition piece as the flow sleeve is moved along the plurality of expander segments; and a circumferentially disposed space separating each pair of adjacent expander segments in the plurality of expander segments.

Abstract: Provided are: a muffler that can suitably obtain an attenuation effect of a sound wave; and a muffling device including the same. The muffler is installed on a wall surface of a pipe conduit where a gas flows. The muffler includes: a front surface exposed to an inner surface of the pipe conduit; a bottom surface facing the front surface; and a side surface disposed between the front surface and the bottom surface and covering a space between the front surface and the bottom surface. The front surface is formed with a plurality of through-holes, and the number of through-holes arrayed in a gas flow direction is one or two, and the number thereof arrayed in a direction orthogonal to the gas flow direction is 10 or more.

Abstract: A system for controlled recovery of thermal energy and conversion to mechanical energy. The system collects thermal energy from a reciprocating engine (for example, from engine jacket fluid) and may also collect further thermal energy from a natural gas compressor (for example, from compressor lubricating fluid). The collected thermal energy is used to generate secondary power by evaporating an organic propellant and using the gaseous propellant to drive an expander in production of mechanical energy. Secondary power is used to power parasitic loads, improving energy efficiency of the system. A supplementary cooler may provide additional cooling capacity without compromising system energy efficiency.

Abstract: A camshaft assembly includes a base shaft including at least one lobe pack axially movably mounted on the base shaft, the lobe pack including a control groove therein. An actuator device includes a pin movably mounted to the actuator between a retracted position and an extended position for engaging with the control groove to cause axial movement of the lobe pack. The control groove includes a pin engagement region, a shifting region and an ejection region. The pin engagement region of the control groove has a first pair of sidewalls. The shifting region extends from the pin engagement region and has a second pair of sidewalls angled relative to the first pair of sidewalls and having a first portion with a varying groove width that varies relative to a groove width of the pin engagement region.

Abstract: Methods and systems are described for an engine with a cam torque actuated variable cam timing phaser. Phaser positioning control is improved by reducing inaccuracies resulting from inadvertent spool valve and/or phaser movement when the spool valve is commanded between regions. In addition, improved spool valve mapping is used to render phaser commands more consistent and robust.

Abstract: A motor control apparatus for adjusting a cam phase includes a motor control part, which controls a current supplied to a stator coil by controlling plural switching elements forming an inverter to turn on and off. The motor control part stops the current supplied to the stator coil each time a motor rotates a predetermined rotation angle interval in a power generation control mode, in which a rotation torque is generated in a direction to impede the motor rotation. The motor control part maintains the power generation control mode when a rotation signal is determined as varying in a predetermined time period. The motor control part switches over an operation mode to a normal control mode to generate a rotation torque in a direction to promote the motor rotation when the rotation signal is determined as not varying in the predetermined time period.

Abstract: In a cogeneration device, a space is formed on a base member that supports an engine and an electric power generator in order to store leakages from the engine in the space. A panel-fixing bracket is provided outside the storage space, at a predetermined distance from a vertical wall section forming a vertical wall of the storage space. A panel, which is a part of a package, is bolted and fixed to the bracket. This structure enables each panel to be fixed to the base member while preventing the leakages stored in the storage space from leaking out.

Abstract: A lubricating oil passage structure for a bearing of an oil cooled rotating machine includes a bearing (114) arranged in the center of a bracket (111) to rotatably support a rotary shaft (101). Protruding ribs (116, 117, 117a) are spirally arranged on the inner surface of the bracket (111). Also, a bearing rib (112) having an oil passage groove (113) for supplying the bearing (114) with lubricating oil is formed on the inner surface of the bracket (111). An upper projection hole (110) is formed in the upper portion of the bracket (111) for introducing the lubricating oil. The protruding ribs located on the right and left of the upper projection hole (110) in the circumferential direction are the upper protruding ribs (116) which function as guides for guiding the lubricating oil to the bearing rib.

Abstract: Disclosed is a blow-by device comprising a connection piece and a coupling piece that can be connected to each other. A ring is provided on which a connector collar for a connector is provided in order to establish an electrical connection in connection pieces that are connected to the coupling piece. The ring may be positioned on the connection piece.

Abstract: An exhaust system for a compression ignition engine comprising: a water adsorbent material; and a catalyst composition for treating an exhaust gas pollutant produced by the compression ignition engine; wherein the water adsorbent material is: (i) arranged to contact exhaust gas from the compression ignition engine before the catalyst composition; and (ii) in thermal communication with the catalyst composition.

Abstract: A flow manifold system for injecting a first gas into a second gas, such as, for example, a system for injecting ammonia gas into the exhaust gas of an internal combustion engine. The first gas may be supplied to the system by one or more cartridges. The system may also include a control valve that is configured to control the delivery of the first gas to the least one critical flow orifice. The critical flow orifice is configured to allow for a relatively constant volumetric flow of the first gas through the critical flow orifice when the first gas attains a critical flow. Such critical flow may allow for an accurate estimation of the flow of the first gas through the critical orifice, and subsequently to the second gas, without the use of a flow sensor.

Abstract: An inlet port (17A) of a first exhaust gas purifying device (16) is provided on a side opposite to an engine (8) by sandwiching an axis (O1-O1) of a cylindrical body (17) of the first exhaust gas purifying device (16). An exhaust pipe (26) connecting the engine (8) and the first exhaust gas purifying device (16) is constituted by a lateral pipe line (27) extending in a left and right direction of an upper revolving structure (3) on a front side of the first exhaust gas purifying device (16) and having a bellows pipe (28) in the middle for absorbing relative displacement between the engine (8) and the first exhaust gas purifying device (16) and a bent pipe line (29) bent having a U-shape rearward from a tip end side of the lateral pipe line (27) and connected to the inlet port (17A) of the first exhaust gas purifying device (16).

Abstract: A deposit detection device for an exhaust pump is provided, which can be easily put into operation without the burdens of, for example, installing equipment for flowing a gas, or adding or changing operation modes in apparatuses.

Abstract: A method is disclosed for regulating an exhaust after-treatment (AT) system for a diesel engine. The method includes detecting the engine's cold start when the engine's exhaust gas flow directed into the AT system is at a temperature below a threshold value. The method also includes determining flow-rates of the engine's exhaust gas and its fuel supply. The method additionally includes determining a magnitude of exhaust gas energy using the determined exhaust gas flow-rates and the fuel supply over an elapsed time following the cold start. The method also includes integrating a detected temperature of the exhaust gas over the elapsed time and comparing the determined magnitude of exhaust gas energy with the integrated temperature. Furthermore, the method includes regulating operation of the AT system using the determined exhaust gas temperature when the determined magnitude of exhaust gas energy is within a predetermined value of the integrated exhaust gas temperature.

Abstract: A disposing method for an inlet pipe in a muffler that includes an outer shell, an inlet pipe, and a separating plate, the disposing method comprising: a first step of inserting the inlet pipe into the outer shell from an opening at one end of the outer shell; a second step of disposing the inlet pipe by moving the inlet pipe within the outer shell in a direction substantially orthogonal to the direction of insertion of the inlet pipe; and a third step of disposing the separating plate by inserting the separating plate into the outer shell from the opening at the other end of the outer shell.

Abstract: The present invention is configured such that: a cylinder block includes an introducing portion provided at a first side of a cylinder row, cooling liquid being introduced through the introducing portion to a water jacket, a restrictor portion provided in a vicinity of the introducing portion and configured to restrict the cooling liquid, introduced through the introducing portion, from flowing to an intake-side portion of the water jacket, and a discharging portion provided at a middle portion of the cylinder row at an intake side, the cooling liquid being discharged from the water jacket through the discharging portion; and an exhaust-side portion of the water jacket is formed such that a passage cross-sectional area of a cylinder axis direction upper side of the exhaust-side portion is larger than the passage cross-sectional area of a cylinder axis direction lower side of the exhaust-side portion.

Abstract: A dump truck includes: a vehicle body; a cooling fan disposed in front of the vehicle body in a travel direction; an engine disposed behind the cooling fan; a platform covering the cooling fan and a top of the engine; an exhaust aftertreatment device disposed behind the engine and above the platform; an opening through which an upper side of the platform communicates with a lower side thereof and provided in front of the exhaust aftertreatment device; and a duct provided to a lower surface of the platform and comprising a base-end opening connected to the opening and a leading-end opening directed to the cooling fan.

Abstract: An internal combustion engine cooling device includes a piston fixedly mounted within a device housing coupled to a plurality of flow paths through which cooling water flows, the piston disposed facing the interior of the device housing; a cylinder container that advances and retreats relative to the piston and has a flange valve that opens and closes a main flow path of the cooling water; a thermal expansion unit provided within the cylinder container that causes the cylinder container to advance and retreat due to volumetric changes attendant upon temperature changes; and a heat-emitting element provided within a piston casing that heats the thermal expansion unit when supplied with electricity. An insulating cover is provided to the exterior of the cylinder container at a portion of the cylinder container disposed facing the cooling water.