Abstract: A multi-stage exhaust turbocharger has parallel high pressure stages (30, 40), and a single low pressure stage (60) in series. The low pressure stage (60) has a divided scroll turbine wheel 62 with each scroll fed independently from the respective turbines of the high pressure stage. Valves V1, V2, V3 determine flow paths to the respective turbines to ensure series sequential operation.

Abstract: A car intercooler pipe includes an inlet of the intercooler pipe positioned at an upper side of the car intercooler pipe, an upper corrugated portion having upper corrugated bodies protruding in a rib shape from a surface of a pipe body extending in a direction toward the inlet, an outlet of the intercooler pipe positioned at a lower side of the car intercooler pipe, a lower corrugated portion, and an intermediate portion bent downward from the upper corrugated portion and having the pipe body connected to the lower corrugated portion, wherein a thickness of the pipe body of the intermediate portion is greater than a thickness of the upper corrugated body of the upper corrugated portion and a thickness of the lower corrugated body of the lower corrugated portion, and wherein disconnection portions having corrugations with different heights are formed in the upper corrugated body and the lower corrugated body.

Abstract: Out of connection passages connecting the engine cooling circuit and the intercooler cooling circuit, a coolant inflow passage is connected between downstream of a mechanical pump and also upstream of a main radiator of the engine cooling circuit, and downstream of a sub radiator and also upstream of an electric pump of the intercooler cooling circuit, and a coolant outflow passage is connected between downstream of the electric pump and also upstream of the sub radiator of the intercooler cooling circuit, and downstream of the mechanical pump and also upstream of the main radiator of the engine cooling circuit. An inter-cooling circuit valve is provided in the coolant inflow passage.

Abstract: A engine system is provided with: a plurality of cylinder groups which burn a gas mixture and discharge an exhaust gas; a plurality of high-pressure stage superchargers each having high-pressure stage turbines driven by the exhaust gas from the corresponding cylinder group and high-pressure stage compressors rotated by driving of the high-pressure stage turbines and configured to compress a gas supplied to the corresponding cylinder group; and a plurality of low-pressure stage superchargers having a low-pressure stage turbine driven by an exhaust gas discharged from the high-pressure stage turbine of the high-pressure supercharger which is any one of the plurality of high-pressure stage superchargers, and a low-pressure stage compressor rotated by driving of the low-pressure stage turbine and configured to compress a gas supplied to the high-pressure stage compressor of the high-pressure stage supercharger other than the one high-pressure stage supercharger.

Abstract: An exhaust gas turbocharger (1) including a compressor housing (2), a bearing housing (3), a turbine housing (4) in which a turbine wheel (5) is arranged, which has a housing inlet (6), which has a turbine spiral (7) connecting to the housing inlet (6), which has a housing outlet (8), and which has a wastegate arrangement (9), which in the open state brings the housing inlet (6) into flow connection with the housing outlet (8) for guiding a wastegate mass flow. The wastegate insert part (10) is arranged in the turbine housing (4) between the turbine wheel (5) and the housing outlet (8) and the open wastegate arrangement (9) introduces the wastegate mass flow into the wastegate insert arrangement (9).

Abstract: A turbine (32) section of a turbocharger (30) includes a turbine wheel (37) disposed in a turbine housing (33), the turbine housing (33) defining a gas inlet (34), a volute configured to direct gas from the inlet (34) to the turbine (32) wheel, and a gas outlet. A rotary diverter valve (100, 200) is disposed in the gas inlet (34) upstream of the volute, and provides three modes of controlling exhaust gas flow about the turbocharger (30).

Abstract: Systems and methods for operating an engine that includes a cavity in an exhaust manifold of a turbocharged engine are described. The systems and methods may improve engine efficiency and provide a way of controlling temperatures of engine exhaust components. The cavity may be located between an exterior wall of the exhaust manifold and an interior wall of the exhaust manifold.

Abstract: A turbine housing assembly can include a turbine housing that includes an exterior surface, an interior surface that includes a wastegate seat, and a bore that extends between the interior surface and the exterior surface; a bushing disposed at least partially in the bore where the bushing includes a bushing bore; a wastegate that includes a shaft that extends through the bushing bore to a shaft end, a shaft shoulder disposed in the bushing bore, a plug, and an arm disposed between the shaft and the plug; a ring disposed at least in part in the bushing bore between the shaft shoulder and the shaft end; and a control arm connected to the shaft proximate to the shaft end to define an axial distance between a surface of the control arm and the shaft shoulder where the ring has an axial length that is less than the axial distance.

Abstract: A method can include positioning a bushing in a bore of a turbine housing; positioning a shaft of a wastegate in a bore of the bushing where the shaft includes a shaft shoulder and a shaft end; applying force to a plug of the wastegate to substantially center the plug with respect to a wastegate seat of the turbine housing; positioning a ring at least in part in the bore of the bushing and between the shaft shoulder and the shaft end; and fixing the ring to the bushing.

Abstract: An exhaust-flow-rate control valve for controlling a flow rate of exhaust gas flowing through an exhaust flow passage includes: a valve rod; a valve body having a flat plate shape and configured to rotate about the valve rod; and a valve housing having a cylindrical shape and defining a part of the exhaust flow passage inside the valve housing.

Abstract: A split-cycle engine includes a compression cylinder having a first volume for a first working fluid and a second volume for a second working fluid, the first volume and second volume being separated by the compression piston, an expansion cylinder having a first volume for the first working fluid and a second volume for the second working fluid, the first volume and second volume being separated by the expansion piston, and a fluid coupling between the second volume of the compression cylinder and the second volume of the expansion cylinder, wherein the two second volumes and the fluid coupling provide a closed volume for the second working fluid, wherein the fluid coupling includes a regenerator arranged such that the two second volumes are thermally decoupled.

Abstract: A method for reforming fuel for an engine is disclosed. The method comprising heating, in a non-catalytic combustor, a mixture of fuel and air at a temperature in a range from 550K to 950K, to partially oxidize the fuel to generate one or more free radicals. The one or more free radicals constitute reformed fuel. Further, the reformed fuel is supplied to the engine.

Abstract: A multi-link piston crank mechanism includes a crank pin bearing portion including a crank pin bearing central portion that is disposed at a center thereof in an axial direction of a crank shaft. The crank pin bearing central portion at a portion positioned on the first end side of the lower link is thicker in a radial direction of the crank pin than a portion positioned on the second end side of the lower link. The second control link end portion is thicker along a radial direction of the second through hole than the second upper link end portion along a radial direction of the first through hole.

Abstract: A shaft-hub connection including a lever; and a bearing element of a connecting rod, wherein the bearing element of the connecting rod is arranged in an opening of the lever, wherein the opening is configured so that at least two contact locations are provided between the lever and the bearing element, wherein a clear space is respectively provided between the at least two contact locations, and wherein the opening is offset from the bearing element in the clear space.

Abstract: A sensor casing includes a lower case and an upper case that is fixed to an upper part of the lower case. A valve body includes an upper body including an accommodation space in which a sensor casing is disposed and a lower body in which an oil passage is formed. The upper body includes a stopper that prevents downward movement of the oil pressure sensor along a central axis. The sensor casing includes an engagement portion that engages with the stopper to retain the oil pressure sensor in the accommodation space.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool and the HP spool are independently rotatable about an axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. The LP compressor is axially positioned between the HP compressor and an accessory gear box (AGB). The AGB is drivingly connected to the HP spool through the center of the LP compressor.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Abstract: An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc.

Abstract: The present disclosure generally relates to separating entrained solid particles from an input airflow in a gas turbine engine. A cyclonic separator receives the input airflow from a compressor and separates a first portion of the input airflow. The cyclonic separator remove solid particles from the first portion of the input airflow to provide a first cleaned airflow to a first cooling system. A clean air offtake downstream from the cyclonic separator separates a second cleaned airflow from a remaining portion of the input air stream and provides the second cleaned airflow to a second cooling system. The remaining portion of the input airflow is provided to a combustor.

Abstract: A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.

Abstract: A gas turbine engine includes a core nacelle and a core engine disposed in the core nacelle. The core engine includes at least a compressor section, a combustor section, and a turbine section, which define a core flowpath. A bypass duct is radially outwards of the core nacelle. A component is disposed in the core engine. A cooling cavity is disposed outside of the bypass duct. A heat pipe contains a working medium sealed therein. The heat pipe includes a first section configured to accept thermal energy and a second section configured to dissipate the thermal energy in the cooling cavity. A tap from at least one of the compressor section or the bypass duct is configured to provide bleed air to the cooling cavity and dissipate the thermal energy from the second section.

Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.

Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.

Abstract: An ignition device of an embodiment is provided to a gas turbine combustor to which supercritical-pressure CO2 is introduced. The ignition device includes: a shutoff valve provided on an outer side face of a casing of the combustor to make the inside of the casing and the outside of the casing communicate with each other or shut off from each other; an ignition rod formed of a long rod including a spark discharge portion at a leading end, and capable of advancing to and retreating from the inside of a combustor liner provided in the casing from/to the outside of the casing through the shutoff valve; and a driving part which makes the ignition rod advance and retreat.

Abstract: A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool and the HP spool are independently rotatable about an axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is axially mounted at one end of the engine. The LP compressor is axially positioned between the HP compressor and the AGB. The AGB is drivingly connected to the HP spool through the center of the LP compressor.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable of one another about an engine axis. The LP spool comprises an LP turbine, an LP compressor and an LP shaft. The HP pressure spool comprises an HP turbine, an HP compressor and an HP shaft. The LP turbine is in fluid flow communication with the HP turbine and disposed downstream therefrom. The HP compressor is in fluid flow communication with the LP compressor and disposed downstream therefrom. The LP shaft has an upstream shaft portion extending upstream of the LP turbine to a location upstream of the LP compressor to provide a first power take-off at an upstream end of the engine and a downstream shaft portion extending downstream of the LP turbine to provide a second power take-off at a downstream end of the engine, thereby allowing mounting of a reduction gear box at either end of the engine.

Abstract: A turbine engine, comprising at least one drive shaft having an axis of rotation A and configured to drive a fan wheel by means of an epicyclic reduction gear train, said reduction gear having: a sun gear configured to be driven by said drive shaft about said axis A, a ring gear surrounding the sun gear and configured to drive a fan shaft about said axis A, and an annular row of planet gears interposed between the sun gear and the ring gear and held by a planet carrier fixed to a stator housing of the turbine engine, said turbine engine also having an electrical apparatus with rotor, wherein the stator of the electrical apparatus is fixed to the stator housing by means of an annular member for apparatus support, the annular member comprising legs of an elongated shape that axially traverse the reduction gear, the annular member comprising at longitudinal extremities of the legs a first annular element for fixing to an annular flange integral with the stator housing, and wherein the stator of the apparatus

Abstract: A system is provided for speed control during motoring of a gas turbine engine of an aircraft. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to adjust the starter air valve to control motoring of the gas turbine engine based on measured feedback with lead compensation to reject disturbances attributable to dual to single or single to dual engine starting transitions.

Abstract: A gas turbine system includes a compressor. The compressor has a plurality of inlet guide vanes disposed at an inlet of the compressor. Furthermore, the compressor may have at least one unison ring coupled to a plurality of variable stator vanes disposed between the inlet and an outlet of the compressor. The gas turbine system includes a first actuator that may adjust a first pitch of the plurality of inlet guide vanes and a second actuator that may adjust a second pitch of the plurality of variable stator vanes. A first electric motor may drive the first actuator, while a second electric motor may drive the second actuator.

Abstract: A control device of an internal combustion engine 100 provided with a compression ratio control part controlling a mechanical compression ratio to a target compression ratio. The compression ratio control part is configured provided with an optimum compression ratio calculating part calculating an optimum compression ratio in an engine operating state based on the engine operating state, a permittable changed compression ratio calculating part calculating a permittable changed compression ratio giving an effect of improvement of the fuel efficiency even considering the amount of fuel consumed by driving a motor when the optimum compression ratio is higher than a target compression ratio, and a target compression ratio changing part changing the target compression ratio to the permittable changed compression ratio if the optimum compression ratio is higher than the target compression ratio and the optimum compression ratio becomes the permittable changed compression ratio or more.

Abstract: According to the present invention an expandable joint is made without removable bearing caps by preassembling eccentric bushings onto the hinge pin. The expandable joint has a hinge type construction, but with the journals for each side of the hinge being spaced apart so that the distance between the two sides of the hinge changes with rotation of the hinge pin. The expandable joint of the present invention is assembled by sliding the hinge pin into the hinged joint with the eccentric bushings attached. Once the hinge pin is in place, the eccentric bushings are locked in place with fasteners so that they do not rotate. After the eccentric bushings are locked in place, the hinge pin can be turned to expand the joint. The expandable joint is intended for use in variable compression ratio engines, where expansion of the joint changes the compression ratio of the engine.

Abstract: A Volatile Organic Compound (VOC) mitigation system employs a combination of technologies coupling VOC laden exhaust with a reciprocating engine and generator system (Combined Heat & Power (CHP) System) with heat recovery to destroy the VOC emissions and generate electric power and useful thermal energy.

Abstract: A single input engine controller and system are provided for translating a single input indicative of the amount of fuel to be supplied to an engine from a fuel control interface into separate signals for controlling the amount of fuel supplied to the engine and the RPM of a propeller powered by that engine. The single input controller translating the single input into the separate signal for the RPM of the propeller according to a fuel efficiency relationship between the fuel amount and the propeller RPM.

Abstract: An engine system incorporating an intake manifold, a compressor, and a controller. The compressor may provide air to the intake manifold and the controller may be connected to the intake manifold and the compressor. The controller may receive a control signal and control air flow from the compressor to the intake manifold based on the received control signal. The controller may control the air flow from the compressor to the intake manifold based on a first equation when a value related to the control signal is on a first side of a threshold and according to a second equation when the value is on a second side of the threshold. The controller may control the air flow between the compressor and intake manifold according to the second equation to prevent the compressor from operating at a surge condition when controlling the air flow according to the first equation.

Abstract: A transport refrigeration system is provided including a refrigeration unit and a diesel engine powering the refrigeration unit. The diesel engine has an exhaust system for discharging engine exhaust from the diesel engine. An exhaust treatment unit is disposed in the diesel engine exhaust system and includes a diesel oxidation catalyst. An air control valve is configured to control a quantity of air provided to the diesel engine from an air supply fluidly coupled to the diesel engine. A controller is operably coupled to the air control valve and is configured to automatically operate the air control valve to initiate a cleaning cycle of the diesel oxidation catalyst upon detection of a predetermined condition.

Abstract: A fuel supply control system for a V-type two-cylinder general purpose engine according to the present disclosure, in a V-type two-cylinder general purpose engine including one fuel injection valve in a throttle body disposed upstream via an intake manifold connected to a cylinder head of each cylinder, changes an injection frequency or an operation timing of the fuel injection valve in accordance with an engine operation state detected by a detection unit.

Abstract: A method to control engine start-stop in a vehicle is provided. The method includes outputting via a controller an engine command to auto-start the engine based on detection of a predetermined vehicle condition affecting fuel economy of the vehicle, detection of a shift from neutral to another gear position, and whether a predetermined time threshold has expired following the shift in response to detection of a presence of an engine auto-stop mode and a neutral gear position. The predetermined vehicle condition may be a movement of the vehicle in a reverse direction. The predetermined vehicle condition may be a battery parameter being outside of predetermined range. The predetermined range may be based on a battery state of charge, a battery temperature, a battery voltage, or a battery load current. The predetermined vehicle condition may be a HVAC component activation.

Abstract: A controller of an air-fuel-ratio sensor includes a control unit, a voltage-abnormality detecting unit, and a short-circuit-abnormality detecting unit. The control unit controls a current and a voltage of a gas sensor element through a plurality of terminals connected with the gas sensor element. The voltage-abnormality detecting unit changes, when at least one of voltages of the plurality of terminals is out of a predetermined range, a voltage level of an output voltage. The short-circuit-abnormality detecting unit causes, when the voltage level of the output voltage changes from a first voltage into a second voltage, a control unit to perform for a predetermined time a protective operation that suppresses currents from the control unit to the plurality of terminals, and detects, when the voltage level of the output voltage is the second voltage after the protective operation is released, a short-circuit abnormality.

Abstract: A controller includes a processor and a memory storing processor-executable instructions. The processor is programmed to receive a signal indicating engine knocking, adjust an octane requirement in response to the signal, and request a fuel for refueling meeting the octane requirement. The processor may also be programmed to avoid a gas station of most recent refueling in response to the signal and retard ignition timing of a spark plug in response to the signal.

Abstract: The present disclosure provides an intake air flow rate measuring device. The intake air flow rate measuring device includes a flange, a casing, a flow rate sensor, a humidity sensing element, an element terminal, and a humidity terminal. The humidity terminal is spaced away from the element terminal. A portion of the casing between the element terminal and the humidity terminal is defined as a suppressing portion, and a cross-section of the suppressing portion is defined as a suppressing portion cross-section. An end portion of the casing close to the flange is defined as a base portion, and a cross-section of the base portion is defined as a base portion cross-section. The suppressing portion cross-section is set to be smaller than the base portion cross-section.

Abstract: Methods and systems are provided for performing rationality check of a hydrocarbon sensor in an evaporative emission control system. In one example, a method may include sensing fuel vapors vented from a fuel vapor canister to atmosphere via the sensor, and performing sensor rationality check by flowing desorbed hydrocarbons from the fuel vapor canister to an engine via the sensor during purging of the fuel vapor canister.

Abstract: The air-fuel ratio feedback control section updates an air-fuel ratio feedback correction value. The air-fuel ratio learning control section performs, in each of learning regions, learning of an air-fuel ratio learning value. If the air-fuel ratio feedback correction value converges to a value less than or equal to a specified value, the air-fuel ratio learning control section determines that learning of the air-fuel ratio learning value in the learning region has been completed. If it has not yet been determined that learning of the air-fuel ratio learning value has been completed in any of the learning regions, the air-fuel ratio learning control section collectively updates the air-fuel ratio learning values of all the learning regions at the time of updating the air-fuel ratio learning value through learning in any of the learning regions.

Abstract: A delay module, based on a base request received for a first loop, sets a delayed base request for a second loop. A first period between the first and second loops corresponds to: a first delay period of an oxygen sensor; and a second delay period for exhaust to flow from a cylinder of an engine to the oxygen sensor. A closed loop module determines a closed loop correction for the second loop based on: the delayed base request for the second loop; a measurement from the oxygen sensor; the closed loop correction for the first loop; and the closed loop correction for a third loop. A second period between the second and third loops corresponds to the first delay period of the oxygen sensor. A summer module sets a final request for the second loop based on the base request plus the closed loop correction for the second loop.

Abstract: Methods and a system are provided for controlling fuel injection in a vehicle engine. The system specifically relates to an engine fueled with both port and direct fuel injectors. In one example, a method may include delivering a first portion of fuel via port injection during a first injection window, and subsequently delivering a second portion of fuel directly during a second injection window before the engine exits cranking speeds.

Abstract: Various methods and systems are provided for health assessments of a fuel system. In one example, a fuel system includes a low-pressure pump operable to pump fuel from a fuel source at a first pressure, a high-pressure pump operable to increase the first pressure to a second pressure, a valve positioned between the low-pressure pump and the high-pressure pump and operable to control fuel flow to the high-pressure pump, a common fuel rail fluidly coupling the high-pressure pump to a plurality of fuel injectors coupled to cylinders of an engine, and a controller. The controller is operable to adjust an amount of valve electrical current supplied to the valve to reach a commanded pressure of the common fuel rail during cylinder firing conditions, the supplied valve electrical current adjusted based on a valve pre-firing correction factor for the valve obtained based on valve electrical current prior to cylinder firing commencing.

Abstract: An injection system for an internal combustion engine including at least one injector and a high-pressure accumulator, which has a fluid connection to the at least one injector on the one side and has a fluid connection to a fuel reservoir via a high-pressure pump on the other side, wherein a suction throttle is associated with the high-pressure pump as a first pressure-setting element. At least two pressure control valves are provided, via which the high-pressure accumulator can be brought into fluid connection with the fuel reservoir.

Abstract: Provided is a control device for an internal combustion engine, the control device enabling the suppression of variations in the amount of fuel injected by injection while the boost voltage is charging, without offsetting the injection timing. A boost circuit (211) boosts a first voltage supplied from a battery (201), and supplies a boosted second voltage to a fuel injection device (214). Switches (212, 213) switch the second voltage supplied to the fuel injection device from the booster circuit on and off. Computation devices (204, 207) control the switches. Each computation device comprises: an estimation unit that, before the initial fuel injection in a combustion cycle, estimates the second voltage for all of the fuel injection times in the combustion cycle; and a correction unit that corrects the amount of fuel injected for each fuel injection time depending on the estimated second voltage.

Abstract: An engine control device is provided which includes a first fuel injection valve; a second injection valve provided at such a position that the amount of fuel injected by the second fuel injection valve and adhering to the inner peripheral wall of a cylinder is smaller; a cooling water temperature detector for detecting the temperature of cooling water for cooling an engine; and an injection ratio determining arrangement for determining the ratio between the amount of fuel injected by the first fuel injection valve and the amount of fuel injected by the second fuel injection valve based on the temperature of cooling water. The injection ratio determining arrangement stores an injection amount adjustment operation range in which the injection ratio determining arrangement is configured to increase the fuel injection ratio of the amount of fuel injected by the second fuel injection valve, when the temperature of cooling water falls.