Abstract: A rotary engine includes an intake port, an exhaust port, a rotor having an intake channel and/or an exhaust channel, and a rotor shaft coupled to the rotor. The rotor shaft has an inflow channel in communication with the intake channel and/or an outlet channel in communication with the exhaust channel. The rotary engine includes a housing having a working chamber formed between the housing and the rotor, the working chamber configured to handle, in succession, an intake phase, a compression phase, a combustion phase, an expansion phase, and an exhaust phase. The inflow channel cyclically communicates with the intake port and forms a passage between the intake port and the working chamber through the rotor shaft and the intake channel. The outlet channel cyclically communicates with the exhaust port and forms a passage between the exhaust port and the working chamber through the rotor shaft and the exhaust channel.

Abstract: An axial fan includes: a hub; a plurality of blades arranged in a circumferential direction of the hub; a cutout in a rear edge part of each of the plurality of blades, the cutout divides the rear edge part into an outer rear edge part and an inner rear edge part; a first groove part disposed in the outer rear edge part, the first groove part including a plurality of grooves extending toward the front edge part; and a second groove part disposed in the inner rear edge part, the second groove part including a plurality of grooves extending toward the front edge part, the plurality of grooves of the first groove part and the plurality of grooves of the second groove part having different shapes when viewed in a rotational axis direction of the hub.

Abstract: An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.

Abstract: An airfoil cooling system (54) for a gas turbine engine (10) is disclosed. The airfoil cooling system (54) may be formed from at least a first cooling fluid supply system (56), and a second cooling fluid supply system (58). The first cooling fluid supply system (56) may be configured to supply cooling fluids at a first pressure to one or more airfoils of a first row (68) of airfoils, and the second cooling fluid supply system (58) may be configured to supply cooling fluids at a second pressure to the one or more airfoils of the first row (68) of airfoils. Additionally, the second pressure may be lower than the first pressure. As such, each of the one or more airfoils may be cooled by cooling fluids at two different pressures. In particular embodiments, this may allow the airfoils to be cooled, while lowering the cost to the turbine engine (10) for providing such cooling.

Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.

Abstract: A turbine rotor blade with a closed loop cooling circuit for an industrial gas turbine engine in which cooling air for the rotor blade is supplied and carried away to and from the rotor blade through the rotor shaft, and where the rotor blade includes a serpentine flow cooling circuit with an even number of legs or channels in which the cooling air is supplied to and discharge from the blade in the blade root. The closed loop rotor blade cooling circuit can be two four-pass serpentine flow cooling circuits or one six-pass serpentine flow cooling circuit.

Abstract: A rotor blade for a turbomachine, in particular in an aircraft engine, with a cooling arrangement for cooling a surface inside the rotor blade by means of a cooling medium, in particular cooling air. The rotor blade having an impingement cooling device with a plurality of impingement cooling openings for deflecting the cooling medium flowing in the interior of the impingement cooling device onto the surface that is to be cooled by means of impingement cooling inside the rotor blade and that is located outside of the impingement cooling device, so that the surface can be cooled by means of an impingement cooling through a cooling medium than exits from the impingement cooling openings, wherein the impingement cooling device is movably mounted with respect to the rotor blade.

Abstract: Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (?A) is furcated (?B, ?C) at each successive vertex juncture.

Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.

Abstract: Disclosed is a turboengine blading member, having at least one platform member and at least one airfoil member. A receiver through opening extends through the platform member. The connector post is received within the receiver through opening. Each of the connector post and the receiver through opening have a retainer flute provided on the circumferential wall and extending along at least a part of the circumferential extent. The retainer flutes are arranged juxtaposed each other with the open sides facing each other such as to jointly form a joint retainer cavity. First and second retainer members are bonded to each other to provide a common retainer member extending into both corresponding retainer flutes, thereby retaining the connector post within the receiver through opening and interlocking the airfoil member and the platform member.

Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.

Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.

Abstract: A seal sub-assembly may comprise a spacer, at least one secondary seal, and a secondary seal cover. At least a portion of the at least one secondary seal are located axially between the spacer and the secondary seal cover. The spacer is attached to the secondary seal cover. The spacer may comprise a first flange and a second flange. The at least one secondary seal may be located axially in line with and radially inward from the first flange. At least a portion of the secondary seal cover may be located axially in line with and radially inward from the second flange.

Abstract: Various embodiments include a system having: a first steam turbine coupled with a shaft; a seal system coupled with the shaft, the seal system including a set of linearly disposed seal locations on each side of the steam turbine along the shaft, each seal location corresponding with a control valve for controlling a flow of fluid therethrough; and a control system coupled with each of the control valves, the control system configured to control flow of a dry air or gas to at least one of the seal locations for heating the system.

Abstract: A method of health monitoring of a gas turbine engine includes mounting a detection system configured to detect an aeromechanical damping characteristic of a row of airfoils of a gas turbine. An actual aeromechanical damping characteristic of the row of airfoils is measured with the detection system. An output signal is generated indicative of the actual aeromechanical damping characteristic of the row of airfoils. A current flutter characteristic is determined based on the output signal indicative of the actual aeromechanical damping characteristic of the row of airfoils. An airfoil health monitoring system for gas turbine engine and a gas turbine engine are also disclosed.

Abstract: The invention relates to the field of compressors, and specifically a compressor stage (100) comprising at least a casing (101) delimiting an air passage (2), a stator (102) comprising a plurality of guide vanes (103) arranged radially around a central axis (X) in the air passage (2), and a rotor (104) suitable for rotating about the central axis (X) relative to the stator (102) and comprising a plurality of blades (105) arranged radially around the central axis (X) in the air passage (2) downstream from the guide vanes (103). Each blade (105) of the rotor (104) extends from a blade root (105a) to a blade tip (105b) further away from the central axis (X) than the blade root (105a) and presents radial clearance (j) between the blade tip (105b) and the casing (101).

Abstract: A vane for a gas turbine engine has a pressure surface and a suction surface. The vane comprises an arrangement of internal channels and a plurality of conducting members extends from the channels towards the suction surface and/or the pressure surface.

Abstract: A gas turbine engine comprising a stator, wherein the stator comprises laminated oscillating heat pipes.

Abstract: Impingement assemblies including an impingement plate having an increased cross-flow structure that forms an increased cross-flow area between the impingement plate and an impingement surface when the impingement plate is installed proximate to the impingement surface. The increased cross-flow structure has a first portion having at least one impingement hole passing through the first portion, the first portion being separated from the impingement surface by an impingement hole height, a second portion separated from the first portion by a separation distance and separated from the impingement surface by a cross-flow structure height, and a third portion extending between the first portion and the second portion. The first portion, the second portion, and the third portion define at least one cross-flow cavity between the impingement plate and the impingement surface, and the cross-flow structure height is greater than the impingement hole height.

Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.

Abstract: A turbine housing includes an inner pipe that forms an exhaust air flow path in which a turbine wheel accommodating a turbine shaft is arranged; and an outer pipe that is spaced from the inner pipe at a predetermined distance and covers the inner pipe. At least one reinforcing plate is secured to an inner surface of the outer pipe.

Abstract: A support device is provided with: a support member having a body disposed in a recess provided in the upper surface of the lower half of an outer member, and a protrusion provided on the body, the protrusion protruding toward the lower half of an inner member from a front surface facing the lower half of the inner member, the protrusion being disposed removably in a hole provided in the lower half of the inner member; a first adjustment member disposed between the bottom surface of the recess and the lower surface, facing the bottom surface, of the body; and an upper liner.

Abstract: An apparatus for lifting an inner casing of a turbine includes a base, an arm, a guide roller, and an adjustment system. The arm has a first end and a second end, and is pivotally connected to the base intermediate the first end and the second end. The guide roller is operatively coupled to the first end of the arm to rotatably engage an exterior surface of the inner casing, and an adjustment system extending from the base and engaging the arm to change an angular position of the arm relative to the base and adjust a position of the guide roller relative to the exterior surface of the inner casing.

Abstract: A gas shield arrangement for a gas turbine engine, the gas shield arrangement comprising: a first gas shield arranged to cover an inlet of a gas flow path of the gas turbine engine; and a second gas shield arranged to cover a first outlet of the gas flow path of the gas turbine engine.

Abstract: a test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.

Abstract: A gas turbine engine fan stand including a base frame and a fan case frame coupled together at one edge by a hinge. The fan case frame is arranged to: rotate about the hinge between abutting the base frame and substantially perpendicular thereto; and tilt about a yaw axis perpendicular to the hinge and in the plane of the fan case frame. The fan case frame further including a coupling arrangement arranged to rotate about a roll axis and to couple a fan case to the fan case frame. A gas turbine engine stand assembly including a fan stand and a core stand. A method of splitting a gas turbine engine and a method of reassembling a gas turbine engine.

Abstract: Transforming any heat sources to electric power, comprising a closed-cycle charged refrigerant loop. Low-pressure refrigerant fluid is pumped at 10 to 15 degrees F. higher of the ambient temperature through a heat exchanger heated by the heat of the gas outlet from the expander then to the boiler (heat exchanger) to boil the refrigerant liquid into a high-pressure and high temperature superheated by a few deg. F. gas (depending on the kind of refrigerant). Heated/pressurized refrigerant gas is inlet into an expander to power an output shaft during the expansion of the pressurized to a cooled gas. Cooled gaseous refrigerant with still high temperature is inlet to small heat exchanger to heat up the pumped liquid refrigerant before inlet to the boiler. The lowered temperature gas is condensed in condenser to liquid at low pressure and 10 to 15 degrees F. higher of ambient temperature media, and recycled by a pump to the heat exchangers.

Abstract: A combined cycle power plant is provided. The combined cycle power plant includes a gas turbine and a heat recovery steam generator disposed in fluid communication with the gas turbine and including one or more steam heater units. Additionally, the combined cycle power plant includes a recuperator unit integrated with the heat recovery steam generator and configured to use gas turbine exhaust from the gas turbine to preheat compressor discharge air from the compressor and supply the preheated compressor discharge air to the combustor, where a first subset of the one or more steam heater units is disposed in parallel to the recuperator unit, and where a second subset of the one or more steam heater units is disposed in series with the first subset of the one or more steam heater units and the recuperator unit with respect to a direction of flow of gas turbine exhaust.

Abstract: A motor drive device for valve timing control of an internal combustion engine includes: a motor drive unit that controls a phase of a camshaft to drive a motor for controlling opening and closing operation of a valve; and a determination unit that determines whether a timing is to start up the motor or to normally drive the motor. The motor drive unit drives the motor with an advance angle when it is determined that the timing is to normally drive the motor by the determination unit, and the motor drive unit normally drives the motor without the advance angle when it is determined that the timing is to start up the motor.

Abstract: A centrifugal separator includes a housing and a rotary vessel having an axis and being attached to the housing for rotation relative to the housing about the axis. Either: a) the rotary vessel has one or more magnetisable regions and the housing has one or more electromagnetic windings; or b) the rotary vessel has one or more electromagnetic windings and the housing has one or more magnetisable regions. The electromagnetic windings are selectively energisable to create a magnetic field to cause rotation of the rotary vessel.

Abstract: An assembly for draining fluid from a sump having a receiver. A plug is adapted for threaded engagement with the receiver, has a transverse outlet arranged for communication with the sump, and is rotatable between: sealed, where flow is inhibited across the outlet; and drain, where fluid from the sump flows across the outlet. A head is rotatably attached to the plug. A limiter between the head and plug operates in: lock, where the head and plug rotate concurrently in a first direction to move the plug from sealed to drain; slip, where the head rotates in a second direction independent of the plug in response to torque acting on the head exceeding a threshold; and limit, where the head and plug rotate concurrently in the second direction in response to torque acting on the head being less than the threshold to move the plug towards sealed.

Abstract: A method of distributing oil to a component within a gas turbine engine includes directing a first oil flow from an oil source to an engine component and back to the oil source, directing a second oil flow from the oil source to a generator driven by the engine and back to the oil source, monitoring a parameter of the second oil flow downstream of the generator and upstream of the oil source, detecting a contaminant in the second oil flow based on the parameter, and reducing the second oil flow to the generator when the contaminant is detected without reducing the first oil flow to the engine component. A shared oil system for a component of a gas turbine engine and a generator driven by the gas turbine engine is also discussed.

Abstract: A drive device for a vehicle with and an exhaust gas tract connected to engine. The exhaust gas tract has a main line with an exhaust gas turbine of a turbocharger and a catalytic convertor downstream of the turbine. The exhaust gas tract has a bypass, by which at least some of the is conductible past a turbine wheel of the turbine such that the exhaust gas is conductible out of the main line at at least one a conducting-out region into the bypass line upstream of the turbine wheel. The bypass exhaust gas flow in the bypass line is conductible into the main line at downstream of the turbine wheel (41) and upstream of the catalytic convertor. To prevent overheating of the catalytic convertor, a cooling device is provided, by which the bypass exhaust gas flow flowing through the bypass line is coolable.

Abstract: An exhaust system for treating an exhaust gas from an internal combustion engine is disclosed. The system comprises a modified lean NOx trap (LNT), a urea injection system, and an ammonia-selective catalytic reduction catalyst. The modified LNT comprises a first layer and a second layer. The first layer comprises a NOx adsorbent component and one or more platinum group metals. The second layer comprises a diesel oxidation catalyst zone and an NO oxidation zone. The diesel oxidation catalyst zone comprises a platinum group metal, a zeolite, and optionally an alkaline earth metal. The NO oxidation zone comprises a platinum group metal and a carrier. The modified LNT stores NOx at temperatures below about 200° C. and releases at temperatures above about 200° C. The modified LNT and a method of using the modified LNT are also disclosed.

Abstract: An exhaust system is for a marine propulsion device having an internal combustion engine. A catalyst housing has a housing inlet end that receives an exhaust gas flow from the internal combustion engine into the catalyst housing and an opposite, housing outlet end that discharges the exhaust flow out of the catalyst housing. A catalyst is disposed in the catalyst housing. The catalyst has a catalyst inlet end that receives the exhaust gas flow and an opposite, catalyst outlet end that discharges the exhaust gas flow. A catalyst mantel is on an outer periphery of the catalyst. The catalyst mantel has a mantel inlet end and an opposite, mantel outlet end. A radial flange is on at least one of the mantel outlet end and mantel inlet end. A connector mates with an inner diameter of the catalyst housing. The radially extending flange of the catalyst mantel is axially sandwiched between the connector and a radially inner shoulder of the catalyst housing.

Abstract: Provided is an exhaust purification system including: an NOx occlusion reduction type catalyst (32), a catalyst temperature estimating unit (115), an NOx occlusion amount estimating unit (113), a regeneration control unit (100) that performs catalyst regeneration of bringing an exhaust gas into a rich state to recover NOx occlusion capacity of the NOx occlusion reduction type catalyst (32), an interval setting unit (118) that sets a target interval from the termination of the catalyst regeneration to a start of next catalyst regeneration, a catalyst regeneration start processing unit (110) that starts the next catalyst regeneration when the NOx occlusion amount is equal to or greater than a threshold and an elapsed time from the termination of the catalyst regeneration reaches the target interval, and an interval target value correcting unit (119) that extends and corrects the target interval based on the NOx occlusion amount when the catalyst temperature is lower than a predetermined catalyst activation temp

Abstract: The embodiments include: a NOx occlusion/reduction catalyst which is provided to an exhaust passage of an internal combustion engine, occludes NOx in exhaust when the exhaust is in a lean state, and reduces and purifies occluded NOx when the exhaust is in a rich state; a NOx purging control unit which, when the exhaust is in the rich state, executes NOx purging in which the NOx occluded in the NOx occlusion/reduction catalyst is reduced and purified; and a NOx-purging-prohibition processing unit which, when at least one of a plurality of prohibition conditions is fulfilled, prohibits execution of catalyst regeneration processing by the NOx purging control unit even if a catalyst-regeneration-processing start request has been issued, and, when one of the prohibition conditions is fulfilled during execution of the catalyst regeneration processing, invalidates the prohibition condition and allows continued execution of the catalyst regeneration processing by the NOx purging control unit.

Abstract: An exhaust purification system is provided with a NOx-occlusion-reduction-type catalyst and a NOx purge rich control unit that executes NOx purge of reducing and purifying the occluded NOx by putting the exhaust into a rich state by fuel injection control, in a case where a catalyst temperature of the NOx-occlusion-reduction-type catalyst is equal to or higher than a catalyst temperature threshold value and a NOx occlusion amount of the NOx-occlusion-reduction-type catalyst is equal to or higher than an NOx occlusion amount threshold value, and executes the NOx purge even when the NOx occlusion amount is less than the NOx occlusion amount threshold value, in a case where the catalyst temperature is equal to or higher than a catalyst temperature threshold value which is greater than the catalyst temperature threshold value.

Abstract: A mixing device for integration into an exhaust pipe of an internal combustion engine and for mixing an exhaust gas stream (T), which device is formed from a housing having a tubular wall and a mid-axis that can be aligned parallel to the exhaust pipe and from an intermediate wall which is aligned transversely with respect to the mid-axis, wherein the intermediate wall divides the housing and has an inflow side and an outflow side, wherein at least one inflow opening (E1) is provided in the intermediate wall, via which the exhaust gas stream (T) can at least partly flow from the inflow side of the intermediate wall to the opposite outflow side of the intermediate wall, wherein the at least one inflow opening (E1) is placed eccentrically with respect to the mid-axis and is brought close to a wall section (W1) of the tubular wall, wherein a flow guide element (S2) having a longitudinal axis (L2) is provided on the outflow side, which at least partly bounds a mixing chamber with the intermediate wall and by an a

Abstract: A heat exchange component including: a pillar-shaped honeycomb structure; and a casing arranged so as to cover an outer circumferential face of the honeycomb structure. The casing includes an inner cylinder arranged so as to be fitted to the outer circumferential face of the honeycomb structure, a middle cylinder arranged so as to cover the inner cylinder, and an outer cylinder arranged so as to cover the middle cylinder such that a circumferential flow path serving as a flow path of a second fluid is formed between the inner cylinder and the outer cylinder. The circumferential flow path includes an inner circumferential flow path and an outer circumferential flow path. At least one communication hole that communicates the inner circumferential flow path and the outer circumferential flow path is formed in a portion of the middle cylinder that covers the honeycomb structure.

Abstract: An internal combustion engine control device including an oxidation catalyst heating value estimation unit 88A, a NOx catalyst heating value estimation unit 88B, an oxidation catalyst temperature estimation unit 88C, a NOx catalyst temperature estimation unit 88D, and switches 801, 802, 803 that switch between an enabled state in which processing performed by the oxidation catalyst heating value estimation unit 88A and the oxidation catalyst temperature estimation unit 88C is executed and a disabled state in which the processing performed by the oxidation catalyst heating value estimation unit 88A and the oxidation catalyst temperature estimation unit 88C is not executed, wherein the control device is configured to be applied to both an exhaust gas purification system including an NOx-occlusion-reduction-type catalyst and an oxidation catalyst and an exhaust gas purification system including the NOx-occlusion-reduction-type catalyst and not including the oxidation catalyst.

Abstract: An exhaust structure for an internal combustion engine has an exhaust pipe having an inner pipe through which exhaust gas of the internal combustion engine circulates, and an outer pipe covering an outer periphery of the inner pipe, and in the exhaust pipe, an inner radiation layer provided on an outer surface of the inner pipe and having a higher emissivity than the inner pipe, an outer radiation layer provided on an inner surface of the outer pipe and having a higher emissivity than the outer pipe, and an intermediate layer proposed between the inner radiation layer and the outer radiation layer, configured to pass infrared radiation therethrough, and having a lower coefficient of thermal conductivity than the inner pipe and the outer pipe are provided.

Abstract: A vortex flow apparatus including a cylindrical housing that contains a fluid that flows in a swirling circular path. The apparatus may be utilized as a muffler for a combustion engine, a particle separator, or an energy conversion device that physically or chemically acts upon the fluid flow and particles contained within the apparatus. The housing defines an inlet opening that opens into the first end of the housing proximate a first end wall. An outlet tube defines an outlet opening through a first end wall. A projection is attached to a second end wall of the housing and extends into the housing. The outlet tube and projection are aligned with and centered relative to a central axis.

Abstract: Provided is a construction machine in which the weight of a top plate of an aftertreatment device mount is reduced without reducing the rigidity of the top plate. In a construction machine where a vehicle body frame for mounting an engine is equipped with an aftertreatment device mount for supporting an exhaust gas aftertreatment device, a mount top plate of the aftertreatment device mount includes a support on which the exhaust gas aftertreatment device is placed, a pair of outer walls extending parallel, a groove portion parallel to the outer walls, a connecting portion provided on the support, and an upper reinforcing member orthogonal to the groove portion at a position of the connecting portion. The upper reinforcing member includes a first reinforcing portion for reinforcing the connecting portion and a second reinforcing portion to be fitted in the groove portion.

Abstract: Methods and systems for cooling a radial engine in a ground-based portable electric power generating system. The engine includes a plurality of cylinders extending radially from a central hub supporting a crankshaft. Each cylinder has a coolant inlet port and a coolant outlet port. The cooling system includes an inlet coolant manifold interconnecting at least two of the coolant inlet ports. The inlet coolant manifold is disposed external to the central hub.

Abstract: A coolant circuit has an engine cooling circuit in which coolant can be circulated in order to cool an internal combustion engine via a cylinder head cooling circuit and a crankcase cooling circuit separated from the cylinder head cooling circuit. The coolant circuit includes a transmission cooling circuit for cooling a transmission, the transmission cooling circuit branching off from the engine cooling circuit. A valve is arranged in the transmission cooling circuit. A controller is designed to open and close the valve depending on an operating state of the internal combustion engine and/or the transmission. In particular, the transmission cooling circuit branches off from the crankcase cooling circuit to a section along which the crankcase cooling circuit is separated from the cylinder head cooling circuit.

Abstract: An ECU includes a motor control unit that controls energization to a motor, and a fixation determination unit that makes a determination on fixation of a valve body. The motor drives the valve body housed in a housing of a control valve. When the fixation determination unit has determined that the valve body is fixed, the motor control unit performs fixation-time control that energizes the motor so as to drive the valve body.

Abstract: A transverse engine adjacent to a drive shaft includes an engine body having a crankshaft, a first pipe connected to the engine body and running such that an engine coolant flows therethrough, and an accessory drive system. The accessory drive system includes an endless outer belt wound between a crankshaft pulley and an alternator drive pulley. A portion of the first pipe forms a water protector located between the drive shaft and the outer belt and overlapping with the outer belt as viewed from the front or rear of the vehicle.

Abstract: A shroud in a heat exchange assembly of a vehicle comprises a housing connected with a radiator of the heat exchange assembly and spaced apart with the radiator; a ventilation aperture disposed on the housing and spaced apart from a fan receiving opening; and a flow guide structure having sidewalls and connected to the housing. The flow guide structure is configured to guide air flow from the ventilation aperture away from a clearance between the housing and the radiator.