Abstract: A method for operating an engine cooling system is provided. The method includes monitoring a coolant temperature profile after engine shut-down and indicating a low coolant level based on the coolant temperature profile determined after engine shut-down.

Abstract: An internal combustion engine includes a pre-chamber. In another aspect, pressure within a pre-chamber is equal to or greater than pressure within a main combustion chamber at least prior to ignition in the main combustion chamber. A further aspect provides a supplemental piston creating pressure and supplying a fuel-air mixture into a pre-chamber, and a spark or glow plug has an end located within the pre-chamber for ignition of the mixture therein. In yet another aspect, internal combustion engine control software automatically controls pressure within a turbulent jet ignition pre-chamber, controls a valve-actuator to admit a fuel-air charge into the pre-chamber, and causes an ignitor to initiate combustion in the pressurized pre-chamber. This also permits the rate of combustion to be controlled in the primary chamber regardless of the air-fuel ratio or the diluent fraction in the main chamber. Another aspect employs a pre-chamber purge pump with separate air and fuel injection.

Abstract: A nozzle for a prechamber assembly of an engine includes a hollow nozzle body having an outer surface, defining first and second outer openings, and an inner surface, defining an interior chamber and first and second inner openings. The nozzle body defines first and second orifices in communication with the interior chamber. The first orifice extends in a first orifice configuration between the first outer opening and inner opening and defines a first entry path projection extending from the first inner opening into the interior chamber. The second orifice extends in a second orifice configuration between the second outer opening and inner opening and defines a second entry path projection extending from the second inner opening into the interior chamber. The first and second entry path projections intersect at an impingement region in the interior chamber, which is radially offset from a central longitudinal axis of the nozzle.

Abstract: Particular embodiments may provide a piston for a prechamber-type gas engine and a prechamber-type gas engine taking into consideration the shape of the piston top surface portion so that the region where flame propagation due to torch jet is delayed, a piston for a prechamber-type gas engine where torch jet formed by combustion a prechamber fuel in a precombustion chamber is injected to a main combustion chamber through a plurality of injection holes, may include a piston top surface portion comprising a land portion formed in a first region extending between axis line directions of adjacent injection holes, and the first region is positioned at a higher position than a second region extending across the axis line direction. The land portion may be formed on a cavity formed in the piston top surface portion.

Abstract: Methods and systems are provided for adjusting operation of an electric motor coupled to a compressor at high altitude engine operation. In one example, the method may include adjusting a ratio of electric compressor assist provided by an electric motor to an intake compressor relative to turbine assist provided via a wastegate during engine idling conditions as well as during transmission gearshifts. The method allows for engine idle speed and torque to be maintained at high altitudes while reducing sluggish boost behavior.

Abstract: Methods and systems are provided for controlling a turbine within an internal combustion engine. In one example, a turbine system within an internal combustion engine may include at least one turbine with a housing that may further include at least one impeller mounted on a rotatable shaft, inlet and outlet regions, and at least one overpressure line including a self-controlling valve for controlling the flow of exhaust gas.

Abstract: A centrifugal compressor for a turbocharger includes a passive or semi-passive inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position solely by aerodynamic forces on the mechanism. The inlet-adjustment mechanism includes a plurality of flexible vanes collectively forming a duct, and an effective diameter of the air inlet at the inducer portion of the compressor wheel is determined by a trailing edge inside diameter of the duct. The vanes are movable solely or in part by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel. The duct has a tapering configuration when the vanes are in a relaxed state, but under aerodynamic force the vanes flex outwardly and increase the trailing edge inside diameter of the duct, thereby increasing an effective diameter of the air inlet.

Abstract: A radial flow compressor includes a device (1, 34) for controlling air flow detachment from the volute tongue (3). The device (1, 34) may include a vane (1) or hole (34) in the tongue (3), and serves to redirect air over the volute tongue (3). The device (1, 34) aids in decreasing the velocity of air flow at the volute tongue (3), diminishes the vortices that develop at the volute tongue (3) from the high air velocities, and redirects air over the volute tongue (3) allowing the air to flow through the narrow passage and attach to the walls of the volute outlet (6).

Abstract: The present subject matter discloses the concept of multiple engine heads for one cylinder operating as Serially Operating Internal Combustion (SOIC) engine using Safe Pipe System (SPS) and other integrated systems, viz., Interim Storage of Gas (ISG) and Pre-Disposal Exhaust Treatment (PDET). SPS is in the form of a chamber having a main pipeline segregated into different interconnected SGC segments allowing and disrupting the flow of substantially pure H2 and substantially pure O2 gas in cold condition through the main pipeline; on receipt of command.

Abstract: An internal combustion engine includes a combustion chamber. The chamber includes a body that is movable in the chamber to vary the chamber volume and contains a catalyst. First valving is operable to admit an intake gas into the chamber and second valving connected with an aqueous fluid supply system is operable to admit an aqueous fluid and a steam reforming fuel into the chamber. A controller is configured to cause the second valving to admit a aqueous fluid and an amount of the steam reforming fuel into the chamber and when a predetermined condition exists in the chamber during compression of the intake gas to absorb heat generated by the compression of the intake gas in the presence of the catalyst to promote a steam reformation process to separate hydrogen from the steam reforming fuel or the aqueous fluid.

Abstract: A genset has an enclosure in which a bulkhead separates the enclosure into a high pressure compartment and a low pressure compartment. A first fan is located in the high pressure compartment and draws ambient air into the high pressure compartment and pressurizes the high pressure compartment to a first pressure that is greater than ambient pressure. A radiator is located within the high pressure compartment such that the pressurized air in the high pressure compartment flows through the radiator and out of the high pressure compartment. A generator is located in the high pressure compartment and provides a gas flow path therethrough from the high pressure compartment to the low pressure compartment. An engine is located in the low pressure compartment and is coupled to the radiator for cooling and is coupled to the generator through the bulkhead to drive the generator.

Abstract: Vehicle engine systems and protectors for such systems are presented. Vehicle engine systems can include one or more engine components associated with an engine. In some embodiments a protector can be attached to an engine system to substantially cover a portion of one or more engine components. The protector can have a shield and a support. In some arrangements, the shield can be operatively connected to two cylinder banks of an engine. The shield can extend over and substantially cover a portion of a fuel line and/or a fuel line connector. In one or more embodiments, the support can include a support end configured to support a vehicle component such as a throttle body.

Abstract: A wave rotor assembly includes a wave rotor combustor and an exit duct. The wave rotor combustor includes an aft plate formed to include an exit port and a rotor drum mounted for rotation relative to the aft plate. The rotor drum is formed to include a plurality of rotor passages arranged to align with the exit port during rotation of the rotor drum. The exit duct is coupled to the aft plate and defines a passage arranged to receive exhaust gasses flowing through the exit port.

Abstract: The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine.

Abstract: A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Abstract: The present invention relates to a method for detecting performance of the lubricant cooler in aircraft auxiliary power unit APU, comprising: acquiring APU-related messages within a time period; obtaining the operation parameters of the APU lubricant cooler, the operation parameters comprise: lubricant temperature OT and load compressor inlet temperature LCIT; the revised lubricant temperature OT is obtained by the following formula: the revised lubricant temperature=lubricant temperature OTA?the load compressor inlet temperature LCIT; determining the performance of the APU lubricant cooler is in stable phase, decline phase or malfunction phase according to the change trend of the revised lubricant temperature OT with respect to time.

Abstract: The gas turbine power generator with two-stage inlet air cooling is a gas turbine power plant for generating electrical power, where air fed into an inlet of a compressor thereof is cooled in a two-stage process. Initially, a heat exchanger receives ambient air and outputs cooled air. An evaporative cooler in fluid communication with the heat exchanger receives the cooled air at a first temperature and outputs cooled air at a second temperature lower than the first temperature. The cooled air at the second temperature is then delivered to a compressor, which is in fluid communication with a combustion chamber for combusting pressurized air with fuel. A gas turbine is in fluid communication with the combustion chamber for receiving heated combustion products therefrom to drive the gas turbine. An electrical generator is in communication with, and is driven by, the gas turbine for producing usable electrical power.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a first compressor having a first overall pressure ratio, and a second compressor having a second overall pressure ratio. A ratio of the first overall pressure ratio to the second overall pressure ratio is greater than or equal to about 2.0. Further, a section of the gas turbine engine includes a thermally isolated area.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling scheme disposed inside the body portion, the cooling scheme including a vascular engineered lattice structure and a heat transfer device adjacent to the vascular engineered lattice structure.

Abstract: A gas turbine equipped with a compressor, a combustion chamber and a turbine is further equipped with: a pressurizing device for taking a portion of the compressed air compressed by the compressor, and pressurizing the compressed air; a combustion chamber cooling line for cooling the combustion chamber using the pressurized compressed air; a temperature regulating line for regulating the temperature of a stationary member of a blade ring or the like of a turbine by using the pressurized compressed air; a combustion chamber supply line through which the compressed air flows from the pressurizing device to the combustion chamber cooling line; a turbine supply line through which the compressed air flows from the pressurizing device to the temperature regulating line; a heater for heating the compressed air, provided in the turbine supply line; and a control device capable of controlling the heater.

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

Abstract: The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operational flexibility and efficiency, and reducing the response time necessary to meet changing demands of an electrical grid. Improvements in power augmentation and engine operation include systems and methods for providing rapid response given a change in electrical grid.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: A gas turbine engine assembly is provided having a gas turbine engine and a fuel supply in flow communication with the gas turbine engine. An accumulator is positioned in flow communication between the fuel supply and the gas turbine engine to store fuel pressure in fuel flowing from the fuel supply to the gas turbine engine.

Abstract: A fuel injection device for a gas turbine, including a plurality of streamlined bodies arranged in a ring adjacent to one another in a circumferential direction relative to a central axis of the fuel injection device, each streamlined body having a trailing edge and at least one streamlined body having a fuel nozzle on the trailing edge, wherein the plurality of streamlined bodies is split into at least a first group of streamlined bodies and a second group of streamlined bodies, all the streamlined bodies in the first group being the same and being different from the streamlined bodies in the second group, and all the streamlined bodies in the second group being the same. The first group of streamlined bodies includes at least two streamlined bodies adjacent to one another. Alternatively, the streamlined bodies are clustered in sets of two adjacent streamlined bodies.

Abstract: An aircraft system is provided that includes a fuel reservoir, a turbine engine and a fuel-to-fuel heat exchanger. The heat exchanger is fluidly coupled between the fuel reservoir and the turbine engine.

Abstract: Apparatus and system for containing a rupture of a duct. The apparatus includes an air-permeable sheet, such as a wide-weave fiberglass sheet. The air-permeable sheet includes a strap arranged on a first side of the sheet such that it forms diamond-shaped patterns along a longitudinal axis. The strap can be made of a tight-weave fiberglass. Laterally-spaced corners of the diamond-shaped patterns include connection members that can be engaged to affix the strap and the air-permeable sheet around a duct. Various aspects include an air-impermeable air barrier surrounding the wide-weave fiberglass sheet and strap. The air barrier can include a window that directs air from a ruptured duct. Various aspects can be used on a bleed-air duct of an aircraft. The window of the air barrier can be aimed at a temperature sensor. A valve can close the bleed-air duct if the temperature sensor detects a high temperature leak.

Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.

Abstract: A method of installing a retaining ring assembly in a turbine case is provided. The method may include installing a blade outer air seal into a case before installation of a retaining ring assembly. The method may further include installing a key system on a retaining ring to create the retaining ring assembly. The method may also include installing the retaining ring assembly in a case. The method may further include rotating the retaining ring assembly in the case until key system is aligned with a case slot. The method may also include tightening the key system to the retaining ring and cause key system to engage the case slot.

Abstract: A gas turbine engine comprises a fan rotor having a hub and a plurality of fan blades extending radially outwardly of the hub. A compressor is positioned downstream of the fan rotor, and has a first compressor blade row defined along a rotational axis of the fan rotor and the compressor rotor. A gear reduction is positioned axially between the first compressor blade row and the fan rotor, and includes a ring gear and a carrier. The carrier has an axial length and the ring gear has an outer diameter. A ratio of the axial length to the outer diameter may be greater than or equal to about 0.20 and less than or equal to about 0.40. The gear reduction is connected to drive the hub to rotate. A method of designing a gas turbine engine is also disclosed.

Abstract: Aspects of the disclosure are directed to an engine of an aircraft. A first duct may be configured to convey a first flow, a second duct may be configured to convey a second flow that corresponds to a first portion of the first flow, and a third duct may be configured to convey a third flow that corresponds to a second portion of the first flow. At least one valve may be configured to control a cross-sectional area associated with at least one of the second duct or the third duct in order to control the ratio of the first portion to the second portion.

Abstract: The present invention relates to a method for detecting performance of an APU fuel assembly, comprising: obtaining APU messages at multiple time points within a time period; obtaining running parameters of the APU fuel assembly according to the APU messages, the running parameters at least comprising starting time STA; calculating average value AVG and deviation index ? of the starting time STA within said time period; determining whether performance of the APU fuel assembly is in the stable phase, decline phase, or failure phase according to the deviation index ?.

Abstract: A variable-geometry system for a gas turbine engine can be used to improve operations in various inclement weather conditions. This may be achieved by varying the orientation of an element in a gas turbine engine flowpath in response to a comparison between sensor-gathered parameter data and stored parameter values and ranges using a pre-programmed algorithm. The orientation of the element may be infinitely variable within a range of orientations.

Abstract: Embodiments of the invention provide a control valve including a control valve body having an inlet passage, an outlet passage, a workport, and a chamber arranged in a fluid path between the workport and the outlet passage. The control valve further includes an annular poppet slidably received within the chamber and to selectively engage a poppet seat to inhibit fluid flow through the fluid path when a pressure in the fluid path is less than a predefined pressure level, and a valve element slidably received within the control valve body to selectively provide fluid communication between the inlet passage and the workport and selectively provide fluid communication between the workport and the outlet passage along the fluid path. The poppet is biased towards the poppet seat by an elastic element.

Abstract: A variable valve operating system assembled in an engine includes a first rocker arm contacting with a valve, a second rocker arm no contacting with any valve, a lost motion spring bringing the second rocker arm into contact with a cam, and switching device for switching the first/second rocker arms to a coupled or uncoupled state. An operation control apparatus for the engine includes element for determining whether or not an engine speed is higher than a first speed at which supply of fuel is allowed to be temporarily stopped, and element for setting a requested quantity of increase/decrease in internal resistance of the engine. When the engine speed is higher than the first speed and an accelerator opening degree is 0%, the switching device switches the first/second rocker arms to the coupled or uncoupled state based on the requested quantity.

Abstract: Method and systems are provided for adjusting an engine load exerted on a vehicle engine by an alternator mechanically coupled to said engine. In one example, a method may include when decelerating a vehicle driven by an engine, recharging a battery by an alternator driven by said engine, and during engine idle speed control, when engine speed is less than desired, in a first mode reducing electrical power to selected devices, and in a second mode offsetting a set point of desired engine ignition timing to a new set point when engine speed is higher than desired.

Abstract: A control system of an engine in which a purge gas containing evaporated fuel desorbed from a canister is supplied to an intake passage of the engine is provided. The control system includes a deceleration fuel cutoff module for performing a deceleration fuel cutoff to stop a fuel supply from an injector to the engine when a predetermined deceleration fuel cutoff condition is satisfied in a decelerating state of the engine, a purge unit for purging by supplying the purge gas to the intake passage during the deceleration fuel cutoff, an O2 sensor provided in an exhaust passage of the engine, an abnormality determining module for determining an abnormality of the O2 sensor based on a change of an output value of the O2 sensor that is caused by the deceleration fuel cutoff, and a purge restricting module for restricting the purge during the abnormality determination.

Abstract: Methods and systems are provided for adjusting an exhaust gas recirculation (EGR) valve based on a final EGR estimate. In one example, a method may include adjusting the EGR valve based on a final EGR flow estimate, the final EGR flow estimate based on a first EGR flow estimated with a differential pressure sensor across the EGR valve, a second EGR flow estimated with an intake oxygen sensor, and accuracy values of each of the first and second EGR flows. The accuracy value may be based on engine operating conditions during estimation of the first and second EGR flows.

Abstract: Methods and systems are provided for determining changes in a flow area of an exhaust gas recirculation (EGR) valve for EGR flow estimates due to soot accumulation on the EGR valve. In one example, a method includes indicating soot accumulation on the EGR valve based on a difference in EGR flow estimated with an intake oxygen sensor and with a pressure sensor coupled across the EGR valve. The determination of the difference of the EGR flow estimates may occur when the engine is not boosted.

Abstract: Methods and systems are provided for determining changes in a flow area of an exhaust gas recirculation (EGR) valve for EGR flow estimates due to a change in temperature difference between a stem and body of the EGR valve. In one example, a method includes adjusting an EGR valve based on an estimate of EGR flow, the EGR flow estimated based on a pressure difference across the EGR valve and an adjusted valve flow area. The adjusted valve flow area may be based on the temperature difference between the stem and body of the EGR valve.

Abstract: A method and apparatus for regenerating a Lean NOx Trap in an internal combustion engine is disclosed. The internal combustion engine includes a Lean NOx Trap, a turbocharger having a turbine. An electronic control unit is configured to execute a regeneration event of the Lean NOx Trap, and regulate a position of an actuator affecting a rotating speed of the turbine using a closed-loop control strategy of an air pressure into an intake duct downstream of a compressor of the turbocharger and upstream of a throttle valve during the execution of the regeneration event.

Abstract: An O2 sensor includes a sensor element using a solid electrolyte layer and a pair of electrodes placed at a position to interpose the solid electrolyte layer, detects an exhaust gas from an internal combustion engine as an object of a detection, and outputs an electromotive force signal depending on an air-fuel ratio of the exhaust gas. The sensor element is connected with a constant current circuit supplying a constant current that is prescribed. A microcomputer calculates a resistance value (element resistance) of the sensor element, and performs a restriction on the constant current supplied by the constant current circuit on the basis of the element resistance.

Abstract: An abnormality diagnosis apparatus is an apparatus that diagnoses a fuel leak from a fuel passage to circulate a liquefied gas fuel between a fuel tank and an internal combustion engine. The abnormality diagnosis apparatus includes: a control device; a low-pressure temperature sensor arranged at a discharge port of a feed pump; and a high-pressure temperature sensor arranged at an overflow fuel emission port of a supply pump. The control device detects a decrease in the temperature of the liquefied gas fuel at the overflow fuel emission port on the basis of a comparison between the measured values of the two temperature sensors, thereby determining that the fuel leak is caused in a section from the discharge port to the overflow fuel emission port.

Abstract: An engine control device includes an engine failure determination unit and a rotation rate control unit. The engine failure determination unit determines whether or not a predetermined failure condition is satisfied based on a result of detection performed by a sensor that detects the state of a marine vessel engine. If an engine rotation rate is higher than a limited rotation rate when the engine failure determination unit determines that the failure condition is satisfied, the rotation rate control unit decreases the engine rotation rate to the limited rotation rate and performs a limited-operation control for rejecting any rotation rate operation that indicates a higher engine rotation rate than the limited rotation rate.

Abstract: The invention relates to a control apparatus of an engine. The apparatus carries out a minute-injection for injecting a minute amount of a fuel so as not to generate an engine torque when a required engine load is zero. The apparatus calculates at least one coefficient for correcting a heat release gravity position calculated when the minute-injection is carried out such that it corresponds to its base position and/or for correcting a heat release rate corresponding the gravity position calculated when the minute-injection is carried out such that it corresponds to its base rate. When the required engine load is larger than zero, the apparatus controls the gravity position corrected by the coefficient to its target position.

Abstract: A correction device for an air/fuel ratio sensor in the present invention, the sensor issuing an output according to an air/fuel ratio and installed on the downstream from catalyst of the exhaust passage, has air/fuel ratio control means for controlling an air/fuel ratio of an exhaust gas on the upstream side from a catalyst to switch between a rich air/fuel ratio which is richer and a lean air/fuel ratio which is leaner than a stoichiometric air/fuel ratio. Moreover, correction means for correcting an output of the sensor in accordance with a difference between the output of the sensor during a predetermined period during air/fuel ratio control by the air/fuel ratio control means, and a reference output corresponding to a stoichiometric air/fuel ratio, is provided.

Abstract: A method for operating a fuel injector, in particular of an internal combustion engine, is described. At least one first injection and one second injection take place in succession. A valve needle reaches its closed position at a first point in time. The triggering of the second injection begins at the first point in time.

Abstract: A method and a device for controlling an internal combustion engine, in particular of a motor vehicle, the internal combustion engine including components which are each operated in an operating mode established by an operating mode coordinator, and it being in particular provided that the operating mode coordinator carries out the aforementioned establishment of at least one operating mode based on further operating aspects of the components.

Abstract: A vehicle includes a port injection valve injecting fuel supplied from a feed pump to engine, and a low-pressure fuel pressure sensor detecting fuel pressure P generated by the feed pump. When a fault diagnosis of the low-pressure fuel pressure sensor is to be conducted, an engine ECU increases fuel pressure P to a diagnosis pressure P2 higher than a normal control pressure P1. Based on whether the output of the low-pressure fuel pressure sensor at this time is a value representing diagnosis pressure P2, the engine ECU determines whether the low-pressure fuel pressure sensor has a fault. In the case where the increase of fuel pressure P to diagnosis pressure P2 has caused excessive fuel (rich air-fuel ratio), the engine ECU changes the engine operating point so that the rotational speed of the engine is decreased while keeping the engine output in order to increase the load ratio.