38th week of 2020 patent applcation highlights part 33 |
Patent application number | Title | Published |
20200291827 | VALVE SEAT INSERT FOR ENGINE HEAD HAVING VENTURI FLOW CROWNS AND SEATING SURFACE PROFILED FOR LIMITING VALVE RECESSION - A valve seat insert for a gas exchange valve such as an intake valve controlling gas exchange of a cylinder includes an insert body having an inner peripheral surface, an outer peripheral surface, and a valve seating surface structured to contact the gas exchange valve at a closed position and profiled to limit valve recession thereof. The valve seating surface includes an arrangement of linear segments and curved segments forming wear crowns to contact the gas exchange valve at different wear states. The valve seat insert is further structured by way of the inner peripheral surface with an incoming flow crown, and a venturi extending from the incoming flow crown toward a throat of the valve seat insert. The venturi accelerates incoming gas flow. | 2020-09-17 |
20200291828 | VALVE CONTROL - A valve control for an internal combustion engine may include a tilt lever, a cam shaft, two cam groups arranged on the cam shaft, a roller bolt arranged on the tilt lever, and an adjusting assembly including a switching pin that engages through the roller bolt. The roller bolt may include two rotatable rollers. The switching pin may be adjustable into a switching position and into a home position. The switching pin may cooperate with a slotted guide of the cam shaft when in the switching position and may have no contact with the slotted guide when in the home position. When the switching pin is in the switching position, the two rollers may be axially adjustable via the adjusting assembly. The switching pin may be axially movable in the roller bolt and the two rollers may be axially movable on the roller bolt into one of two roller positions. | 2020-09-17 |
20200291829 | VALVE TRAIN OF AN INTERNAL COMBUSTION ENGINE - A valve train may include a camshaft, a cam sleeve adjustable in an axial direction between first and second positions and non-rotatably arranged on the camshaft, a first cam and at least one second cam, a pin and at least one cam follower mounted thereon, a guide contour arranged on the cam sleeve and having first and second guide tracks, and a control pin optionally engaging in the first or second guide track to adjust the cam sleeve between the first and second positions. The at least one cam follower in the first and second positions may interact respectively with the first and second cams. On the camshaft or an internal surface of the cam sleeve, first and second snap-in recesses and a third snap-in recess therebetween may be arranged. A snap-in device having a snap-in element preloaded into the snap-in recesses may be provided, the snap-in recess fixing the cam sleeve in the first or second position. The first and second guide tracks may intersect in an intersection region. Between the first and third snap-in recesses and between the second and third snap-in recesses, first and second snap-in humps may respectively be arranged. The snap-in element may engage in the third snap-in recess when the control pin is in the intersection region. | 2020-09-17 |
20200291830 | SLOTTED GUIDE - The present disclosure concerns a slotted guide of a valve train of an internal combustion engine. The slotted guide includes two guide tracks, which cross one another in a crossing region, for guiding a switching pin of a cam follower of the valve train. The two guide tracks have an on-track region, a crossing region, and an off-track region. At least one radial projection, structured and arranged to protrude beyond the slotted guide in a radial direction, is provided in or downstream from the off-track region of at least one guide track. | 2020-09-17 |
20200291831 | VALVE TRAIN OF AN INTERNAL COMBUSTION ENGINE - A valve train of an internal combustion engine may include a camshaft, first and second cams, a rocker arm assembly having a displacement bolt, which may be adjustable between at least first and second positions in the axial direction and on which at least one cam roller, may be mounted in an axially fixed and rotatable manner, wherein the displacement bolt may be mounted in associated bearing lugs of the rocker arm assembly, a guide contour arranged on the camshaft and having first and second guide tracks, a switching pin, which may be arranged in the displacement bolt and which may optionally engage with the first or second guide track to adjust the displacement bolt between the first and second positions. In the first and second positions, the cam roller may cooperate with the first and second cams, respectively. First and second catch recesses may be provided on the displacement bolt. A catch device may engage with a catch element, which may be biased into the first or second catch recess and which may secure the displacement bolt in the first or second position. The first and second guide tracks may cross one another in a crossing region. A third catch recess may be provided between the first and second catch recesses, wherein a first catch protuberance may be arranged between the first and the third catch recesses, and a second catch protuberance may be arranged between the second and the third catch recesses, wherein the catch element may engage with the third catch recess in the crossing region. | 2020-09-17 |
20200291832 | INVERTED NON-STOP APPARATUS OF MULTI-CYLINDER DIESEL ENGINE FOR FREE-FALL LIFEBOAT - An inverted non-stop apparatus of a multi-cylinder diesel engine for a free-fall lifeboat is provided. The apparatus includes a lubricating system and a breathing system. The lubricating system includes a machine body ( | 2020-09-17 |
20200291833 | INTERNAL COMBUSTION ENGINE FOR A MOTOR VEHICLE - An internal combustion engine for a motor vehicle includes a crankcase ventilation device for removing blow-by gas from a crankcase, a pressure sensor being provided for measuring the gas pressure in said crankcase, and a control unit connected to and in communication with the crankcase ventilation device being configured and/or programmed to run a tightness test for said crankcase ventilation device when the internal combustion engine is switched off. | 2020-09-17 |
20200291834 | LUBRICATING OIL SUPPLY STRUCTURE - A lubricating oil supply structure includes: a shaft; a bearing supporting the shaft and having an oil supply port, through which lubricating oil is supplied to between the shaft and the bearing, and an oil introduction port, through which the lubricating oil is introduced; a first oil passage, connected to the oil supply port, distributing the lubricating oil from an oil pump toward the oil supply port; a second oil passage, connected to the oil introduction port, supplying the lubricating oil introduced through the oil introduction port to a supply destination; a connection oil passage, formed by a gap between the bearing and the shaft, connecting between the first oil passage and the second oil passage, and a throttle portion, formed on a part of the connection oil passage, suppressing a flow of the lubricating oil from the oil supply port toward the oil introduction port. | 2020-09-17 |
20200291835 | Fluid System - In one embodiment, there is provided a dock for a replaceable fluid container for an engine, the fluid container having: a fluid reservoir; and at least one fluid port having a coupling adapted to couple with a fluid circulation system associated with the engine; the dock having: a fastening mechanism configured to cooperate with the container such that, as the container is inserted into the dock, the fastening mechanism acts first to seat the fluid container in the dock but in an undocked condition and then, as the container is inserted further into the dock, acts to bring the fluid container into an engaged condition in which the fluid container is docked with a docking interface of the dock. | 2020-09-17 |
20200291836 | COVER FOR OIL FILTER HOUSING OF AN INTEGRATED DRIVE GENERATOR - A cover for an oil filter housing is disclosed comprising an elongated body defining an upper end portion and an lower end portion, and having a central axis extending therethrough, which delineates an axial length of the body, wherein an axial bore extends through the body of the cover from the lower end portion thereof to an interior end wall in the upper end portion thereof for accommodating an axial portion of an oil filter located within the housing, the axial bore of the body having an axial length that is about 90% to about 94% of the axial length of the body. | 2020-09-17 |
20200291837 | EXHAUST SYSTEM FOR AN INTERNAL COMBUSTION ENGINE OF A MOTOR VEHICLE AS WELL AS MOTOR VEHICLE - An exhaust system for an internal combustion engine of a motor vehicle includes an exhaust-gas line and an associated active silencing device. A sound coupling-in line of the silencing device substantially concentrically surrounds the exhaust-gas line on the outside. A first perforation is provided in an axial portion facing away from a sound line in an area of the exhaust-gas line enclosed by the sound coupling-in line. An axial portion facing the sound line is designed perforation-free at least in a portion. Furthermore, a motor vehicle with such an exhaust system is explained. | 2020-09-17 |
20200291838 | METHODS AND SYSTEMS FOR EXHAUST EMISSION CONTROL - Methods and systems are provided for a low temperature NOx adsorber (LTNA). In one example, a method includes operating in a first mode, the first mode including storing exhaust NOx in an LTNA, heating the LTNA until an LTNA outlet temperature reaches a first threshold temperature, and then converting released NOx in a downstream selective catalyst reduction (SCR) device; and operating in a second mode, the second mode including heating the LTNA until the LTNA outlet temperature reaches a second threshold temperature, higher than the first threshold temperature, and converting exhaust NOx in the SCR device. | 2020-09-17 |
20200291839 | METHODS AND SYSTEMS FOR EXHAUST EMISSION CONTROL - Methods and systems are provided for a low temperature NOx adsorber (LTNA). In one example, a method includes initiating a desulfation of an LTNA responsive to an estimated sulfur exposure exceeding a threshold, the desulfation including heating the LTNA to a first threshold temperature while maintaining an exhaust oxygen level above a threshold level throughout the entire desulfation. | 2020-09-17 |
20200291840 | ELECTRIC HEATING TYPE SUPPORT, EXHAUST GAS PURIFYING DEVICE, METHOD FOR PRODUCING ELECTRIC HEATING TYPE SUPPORT, JOINED BODY, AND METHOD FOR PRODUCING JOINED BODY - An electric heating type support includes: an electrically conductive honeycomb structure including a pillar shaped honeycomb structure portion composed of conductive ceramics, the pillar shaped honeycomb structure portion including: an outer peripheral wall; and porous partition walls disposed on an inner side of the outer peripheral wall, the porous partition walls defining a plurality of cells, each cell penetrating from one end face to other end face to form a flow path; and a pair of metal terminals disposed so as to face each other across a central axis of the pillar shaped honeycomb structure portion, each metal terminal being joined to a surface of the electrically conductive honeycomb structure via a welded portion so as to follow a surface shape of the electrically conductive honeycomb structure. | 2020-09-17 |
20200291841 | ELECTRIC HEATING TYPE SUPPORT, EXHAUST GAS PURIFYING DEVICE, AND METHOD FOR PRODUCING ELECTRIC HEATING TYPE SUPPORT - An electric heating support includes an electrically conductive honeycomb structure having an outer peripheral wall and porous partition walls disposed on an inner side of the outer peripheral wall, the porous partition walls defining a plurality of cells, each cell penetrating from one end face to other end face to form a flow path. A pair of metal terminals are disposed so as to face each other across a central axis of the honeycomb structure, each metal terminal being joined to a surface of the honeycomb structure via a welded portion. The honeycomb structure is composed of ceramics and a metal. The honeycomb structure contains 40% by volume or less of the metal. The welded portion of the honeycomb structure has a surface containing 40% by volume or more of the metal. | 2020-09-17 |
20200291842 | Regeneration of Automotive Exhaust Aftertreatment Device Using Diverted Boost Air During Deceleration - A method, used with an internal combustion engine, of providing fresh air for regeneration of an exhaust aftertreatment device. An air intake diversion line is installed from a point between the throttle and the compressor to a point upstream of the exhaust aftertreatment device. A valve on this diversion line is normally closed. If the engine temperature is above a certain threshold and if the engine is in a “high load deceleration” state, the valve is opened, which diverts fresh air to the exhaust aftertreatment device. The valve is then closed after the pressure in the intake line is relieved. | 2020-09-17 |
20200291843 | ATTACHMENT STRUCTURE FOR EXHAUST GAS SENSOR - An attachment structure for an exhaust gas sensor ( | 2020-09-17 |
20200291844 | Two-Cycle Diesel Engine Configured for Operation with High Temperature Combustion Chamber Surfaces - A 2-cycle, direct-injection diesel engine configured to accommodate low cetane diesel and jet fuels. The engine includes combustion chambers having surfaces which are operable at high temperatures during engine operation to increase the combustion rate of low cetane fuels. The engine is further configured to reduce starting times in cold and/or low pressure situations such as those experienced during attempts to restart a plane engine at relatively high altitudes. | 2020-09-17 |
20200291845 | Arrangement Structure of Cooling System in Construction Equipment - In the cooling system of construction equipment equipped with a plural number of heat exchangers including radiators, in providing a pressurized sealed type reservoir tank connected in parallel with radiators in the cooling water circulation system between the radiators and engine, said reservoir tank is arranged so as not to protrude upward exchanger other than radiator is set to be as the upper tier heat exchanger, and the radiator and oil cooler other than the above heat exchanger are arranged lower than the upper tier heat exchanger, and the horizontal width of inter-cooler thus arranged is made shorter than the horizontal width of radiator and oil cooler, and the tank space is formed laterally to the inter-cooler and thus pressurized sealed type reservoir tank is arranged for said tank space. | 2020-09-17 |
20200291846 | CONCRETE MIXER VEHICLE - An engine module for a mixer vehicle includes an engine, a cooling system, and a hood. The cooling system includes a radiator fluidly coupled to the engine and a fan assembly. The fan assembly includes a fan. The hood includes a housing and a door. The housing has a first end configured to be positioned proximate a mixer drum assembly and a second end configured to be positioned proximate a rear end of a chassis of the mixer vehicle. The housing defines an internal cavity within which the engine and the cooling system is disposed. The first end defines an inlet airflow cavity having a bottom surface and an air inlet. The second end defines an opening. The door is pivotally coupled to the second end and positioned to selectively enclose the opening. | 2020-09-17 |
20200291847 | DIFFUSER AND TURBOCHARGER - A diffuser includes a connection section and a body section. The connection section extends from an outlet of turbine rotor blades. The body section is connected to an end of the connection section on a downstream side and has a larger flow passage sectional area than the connection section. The shape of the flow passage sectional surface of the connection section is formed into a circle at an outlet of the turbine rotor blades and is formed into an ellipse at an inlet of the body section. The shape of the flow passage sectional surface of the connection section is further formed to be gradually enlarged in a long-axis direction of the ellipse from the outlet of the turbine rotor blades toward the inlet of the body section. | 2020-09-17 |
20200291848 | Power and miles per gallon for an automotive engine by using 2 stroke technology where the lubrication of the engine parts is independent of the fuel system. - The present invention provides a system and method for providing a wheel fuel efficiency improvement of at least 30% in a gasoline internal combustion engine, the system including a two-stroke engine, a crank case and oil pump in fluid communication with said two-stroke engine but independent of the fuel system of the engine and at least one of a turbocharger and/or another means of providing compressed air in fluid communication with a combustion chamber in said two-stroke engine, wherein camshafts are required to rotate at the same number of revolutions per minute as the crankshaft and that the gasoline can be injected directly into the combustion chamber and will not enter the combustion chamber via an intake manifold. | 2020-09-17 |
20200291849 | Turbocharger Turbine Wastegate Assembly - A turbocharger turbine wastegate assembly can include a lever that includes an opening and two arms, where each of the two arms extends a respective length from the opening; and a crank that includes a wastegate shaft coupling, where the lever and crank are operatively coupled via one of the arms by a pin received in a channel. | 2020-09-17 |
20200291850 | WASTEGATE ASSEMBLY FOR A TURBOCHARGER - A wastegate assembly for a turbocharger having a turbine casing has a wastegate flap, a wastegate flap lever, a wastegate spindle and a bearing bush for the wastegate spindle. In addition, the wastegate assembly has a sealing unit formed from a soft-material volume sealing ring and a diaphragm spring that contacts the volume sealing ring. | 2020-09-17 |
20200291851 | TURBOCHARGER HAVING ADJUSTABLE-TRIM CENTRIFUGAL COMPRESSOR INCLUDING DIVERGENT-WALL DIFFUSER - A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates. The compressor includes a diffuser extending between an exducer of the compressor wheel and a volute for collecting pressurized air from the compressor. The diffuser is defined between first and second walls that diverge from each other in a radially outwardly direction through the diffuser. The divergent-wall diffuser enhances the shift of the surge line to lower flow rates when the inlet-adjustment mechanism is put in the closed position. | 2020-09-17 |
20200291852 | COMPRESSOR HAVING AN ADJUSTMENT MECHANISM - This invention relates to a compressor | 2020-09-17 |
20200291853 | Pulse drive - A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: ▪a combustion chamber ( | 2020-09-17 |
20200291854 | AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM - An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature. | 2020-09-17 |
20200291855 | SYSTEMS AND METHODS FOR DRY FOG INLET PARTICLE SEPARATOR - An inlet particle separator system for a gas turbine engine includes a separator manifold. The separator manifold includes an inlet upstream from an outlet. The inlet is to receive an incoming airflow, and the outlet is to be fluidly coupled to an inlet of the gas turbine engine. The inlet particle separator system includes at least one dry fog nozzle coupled proximate the inlet so as to face at least partially away from the inlet. The dry fog nozzle is external to the separator manifold, and the dry fog nozzle is to direct a spray of dry fog in a direction transverse to the incoming airflow to agglomerate with fine particles in the incoming airflow to form agglomerated particles. The inlet particle separator system includes a scavenging system coupled to the separator manifold downstream from the inlet, and the scavenging system removes the agglomerated particles from the separator manifold. | 2020-09-17 |
20200291856 | APPARATUS FOR SELECTIVE DELIVERY OF PRESSURISED GAS - Apparatus for selective delivery of pressurised gas comprises a containment wall which at least partially bounds of a volume of pressurised gas during use of the apparatus, and a valve directly coupled to an output port of the containment wall such that the containment wall and the valve retain the pressurised gas when the valve is closed. The apparatus obviates the need for a duct coupling the output port to the input of the valve, and hence reduces the number of interfaces between the output port and the input of the valve from two, as in arrangements of the prior art, to one. The apparatus presents fewer failures modes compared to the case where a duct couples the output port to the valve. | 2020-09-17 |
20200291857 | SYSTEMS AND METHODS FOR OPERATING A TURBINE ENGINE - A turbine system includes a compressor section, an inlet cooling system coupled upstream of the compressor section and configured to cool ambient air entering the compressor section, and a turbine section coupled in flow communication with the compressor section and including at least one hot gas path component. The system further includes a controller configured to receive feedback parameters indicative of a temperature of the at least one hot gas path component, estimate a remaining life of the at least one hot gas path component based on the received feedback parameters, determine a desired power output of the turbine system based on the estimated remaining life of the at least one hot gas path component and a cooling capacity of the inlet cooling system, and control operation of the turbine system to cause the turbine system to generate the desired power output. | 2020-09-17 |
20200291858 | DIFFUSER CASE MIXING CHAMBER FOR A TURBINE ENGINE - A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section. | 2020-09-17 |
20200291859 | LOW NOISE TURBINE FOR GEARED GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed. | 2020-09-17 |
20200291860 | BOWED ROTOR START MITIGATION IN A GAS TURBINE ENGINE USING AIRCRAFT-DERIVED PARAMETERS - A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range. | 2020-09-17 |
20200291861 | SEAL FOR A GAS TURBINE ENGINE - A seal for a rotor stack includes a first portion that includes a shaft contact surface. A second portion includes a rotor disk contact surface. A transition portion connects the first portion and the second portion. The transition portion extends radially outward from the first portion. | 2020-09-17 |
20200291862 | CORE DUCT ASSEMBLY - A core duct assembly for a gas turbine engine, the core duct assembly including: a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade. | 2020-09-17 |
20200291863 | HYDRAULIC UNIT GEAR SHROUDS - A gear shroud arrangement includes a plate defining an aperture therethrough. A riser tube has a first end and an opposed second end. The first end of the riser tube is connected to the plate and is aligned with the aperture. A mounting flange extends from the second end of the riser tube. A shroud member extends from the plate in a direction opposite the riser tube. | 2020-09-17 |
20200291864 | HYDRAULIC UNIT GEAR SHROUDS - A gear shroud arrangement includes a plate defining an aperture therethrough. A riser tube has a first end and an opposed second end. The first end of the riser tube is connected to the plate and is aligned with the aperture. A mounting flange extends from the second end of the riser tube. A shroud member extends from the plate in a direction opposite the riser tube. | 2020-09-17 |
20200291865 | GEARED GAS TURBINE ENGINE - A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft. | 2020-09-17 |
20200291866 | GAS TURBINE ENGINE - A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor. | 2020-09-17 |
20200291867 | FUEL MANIFOLD COOLING - A gas turbine engine comprising an engine core comprising a compressor; a compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; and a combustor comprising a fuel manifold configured to provide fuel to the combustor; wherein the fuel manifold is in thermal contact with a cooling conduit; and the gas turbine engine further comprises a fluid conduit to supply bleed air from the compressor bleed valve to the cooling conduit. | 2020-09-17 |
20200291868 | LOUVRE SYSTEM - A louvre assembly ( | 2020-09-17 |
20200291869 | AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM - An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position. | 2020-09-17 |
20200291870 | SYSTEMS AND METHODS FOR CONTROL OF ENGINE VARIABLE GEOMETRY MECHANISM - Methods and systems for controlling an engine having a variable geometry mechanism are described. An output power of the engine is determined. A speed of the engine is determined. A temperature-independent position control signal for the variable geometry mechanism is generated based on a power-to-speed ratio, the power-to-speed ratio obtained by dividing the output power by the speed. The position control signal is output to a controller of the engine to control the variable geometry mechanism. | 2020-09-17 |
20200291871 | GAS TURBINE ENGINE AND CONTROL METHOD - A method of controlling a gas turbine engine capable of operating in at least a high, medium-high, medium, medium-low, and low output power ranges. The method includes during the medium-high output power range varying the angle of the variable guide vanes so that a third predetermined temperature of the combustor is maintained, during the medium output power range the variable guide vanes are closed and bleeding a gas from a downstream part of the compressor to an upstream part of the compressor so that a first predetermined temperature of the combustor is maintained, during the medium-low output power range the variable guide vanes are closed and bleeding a gas from a downstream part of the compressor to an upstream part of the compressor and bleeding a gas from the downstream part of the compressor to the exhaust so that a second predetermined temperature of the combustor is maintained. | 2020-09-17 |
20200291872 | FUEL CONTROL DEVICE, COMBUSTOR, GAS TURBINE, FUEL CONTROL METHOD, AND PROGRAM - A fuel control device includes a stem fuel valve opening degree determination unit, a branch line flow rate determination unit, and a correction value determination unit. The stem fuel valve opening degree determination unit is configured to determine an opening degree of a flow rate adjustment valve of a stem fuel supply line. The branch line flow rate determination unit is configured to determine the opening degree of each flow rate adjustment valve of the branch line based on an operation situation of the gas turbine. The correction value determination unit is configured to determine a correction value of the opening degree of each flow rate adjustment valve of the branch line based on a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet. | 2020-09-17 |
20200291873 | ELECTRONICALLY CONTROLLED THROTTLE CONTROL DEVICE - In an electronically controlled throttle control device in which a throttle control output command calculated by an electronic control unit (ECU) is calculated based on a throttle main control command, calculated from a throttle opening deviation which is a difference between a throttle opening command and a throttle opening detection signal, and a throttle correction control command which is a value obtained by integrating a product of the throttle opening deviation and a coefficient, the coefficient for calculation of the throttle correction control command is changed depending on a driving state based on an acceleration state and a deceleration state of a throttle and a small throttle deviation state. | 2020-09-17 |
20200291874 | ENGINE - Provided is an engine, including: a cylinder including a cylinder liner; a piston provided inside the cylinder liner; a piston ring provided on the piston; a contact detector configured to detect a contact between a step formed in an inner peripheral surface of the cylinder liner and the piston ring; and a compression ratio controller configured to control a top dead center position of the piston so that the piston ring at the top dead center position is located on a combustion chamber side with respect to the step when the contact is detected. | 2020-09-17 |
20200291875 | COMBUSTION CONTROL SYSTEM AND METHOD FOR SWITCHING BETWEEN SPARK AND PILOT-IGNITED OPERATING MODES IN DUAL FUEL ENGINE - A method of controlling a dual fuel engine system includes adjusting a phasing control parameter such as air-fuel ratio (AFR), based on a phasing signal to limit an error in a phasing of combustion of gaseous fuel. The cylinder is switched to a dual fuel liquid pilot-ignited mode by commanding direct injection of an early pilot shot of liquid fuel, based on the adjustment to the phasing control parameter, and production of a spark to ignite gaseous fuel in the cylinder. Switching the cylinder to the dual fuel liquid pilot-ignited mode is completed by commanding direct injection of an early pilot shot and a second pilot shot of liquid fuel to ignite gaseous fuel in response to combustion of the early and second pilot shots in the cylinder. | 2020-09-17 |
20200291876 | Engine - An engine operable in a premixed combustion system and a diffusion combustion system. The engine includes a main fuel injection valve, a pilot fuel injection valve, a liquid fuel tank, a main fuel supply path, a pilot fuel supply path, a pilot fuel filter, a pilot fuel high-pressure pump, a pilot fuel tank, and a pilot fuel supply pump. The pilot fuel tank stores pilot fuel sent from the pilot fuel high-pressure pump and not injected by the pilot fuel injection valve. This pilot fuel is sent to an automatic backwash filter and a pilot fuel filter while not passing through the liquid fuel tank. | 2020-09-17 |
20200291877 | AGGRESSIVE THERMAL HEATING TARGET STRATEGY BASED ON NOX ESTIMATED FEEDBACK - A method for controlling an engine thermal target setpoint, includes: identifying in a first step an initial NOx integral at an initial calculated cylinder wall temperature and a thermal set point of an engine coolant; initiating a command in a second step to change the initial cylinder wall temperature and to change the thermal set point of the engine coolant; creating in a third step a new NOx integral at a new cylinder wall temperature and a modified thermal set point of the engine coolant; and comparing in a fourth step: is (the new NOx integral minus the initial NOx integral) greater than a predefined minimum threshold; and is (the new NOx integral minus the initial NOx integral) less than a predefined maximum threshold. | 2020-09-17 |
20200291878 | CONTROL UNIT OF INTERNAL COMBUSTION ENGINE - A controller of an internal combustion engine includes a sensor, a control unit controlling the engine, and a detector obtaining detection data from the sensor and transmitting the data to the control unit. The detector includes a detection data obtainer obtaining the detection data and storing the detection data in a storage upon having an input of a trigger signal, and a detection data transmitter transmitting the detection data stored in the storage to the control unit, and the control unit includes a trigger output unit outputting the trigger signal at a certain rotation angle timing of the internal combustion engine, and a detection data receiver obtaining the detection data from the detector. | 2020-09-17 |
20200291879 | SYSTEMS AND METHODS FOR DIAGNOSING EJECTOR SYSTEM DEGRADATION FOR DUAL-PATH PURGE ENGINE SYSTEMS - Methods and systems are provided for conducting an ejector system diagnostic under conditions where an engine of a vehicle is not combusting air and fuel. In one example, a method comprises directing a positive pressure to the ejector system while the engine is off in order to communicate a negative pressure with respect to atmospheric pressure on a fuel system and an evaporative emissions system of the vehicle, and indicating that the ejector system is degraded responsive to the negative pressure not reaching a vacuum build threshold. In this way, the ejector system may be diagnosed under conditions where boosted engine operation is infrequent and/or of durations insufficient for conducting such an ejector system diagnostic. | 2020-09-17 |
20200291880 | EXHAUST GAS TREATMENT SYSTEM, AND METHOD FOR HEATING AN EXHAUST GAS CATALYTIC CONVERTER - An exhaust gas treatment system ( | 2020-09-17 |
20200291881 | ENGINE FUEL SUPPLY CONTROL STRATEGY - In at least some implementations, a method of controlling a fuel-to-air ratio of a fuel and air mixture supplied to an engine, includes the steps of determining an engine deceleration event, determining the number of engine revolutions required for the engine speed to decrease from one speed threshold to another speed threshold, comparing the number of engine revolutions determined above against a revolution threshold, and making the fuel and air mixture richer if the number of engine revolutions determined above is greater than the revolution threshold. The method may also include determining if, before the engine stabilized at a stable engine speed (which may be an engine idle speed), the engine speed decreased below the stable engine speed as the engine decelerated to the stable engine speed from a speed above the stable engine speed, and making the fuel and air mixture leaner if the determination is affirmative. | 2020-09-17 |
20200291882 | ENGINE GENERATOR - An engine generator, comprising an engine, a power generator configured to generate electric power based on motive power of the engine, a cooling fan configured to generate a cooling wind for cooling the engine, a control panel configured to accept an operation input by a user, a storage chamber configured to store a constituent part of the control panel, a sensor unit configured to detect a predetermined gas in the storage chamber, and a controller configured to stop the engine based on a detection result of the sensor unit, wherein the storage chamber stores the sensor unit and communicates with outer air such that a gas in the storage chamber can be suctioned by the cooling fan. | 2020-09-17 |
20200291883 | SYSTEM AND METHOD FOR CONTROLLING FUEL SUPPLIED TO AN ENGINE - Systems and methods for determining fuel delay in a fuel injected engine with cylinders that may be deactivated are presented. In one example, the fuel injection delay is determined via a cylinder firing schedule array when the cylinder firing schedule array is available. The fuel injection delay is determined via weighted average of a fuel injection delay of a present engine cycle and a fuel injection delay of a past engine cycle when the cylinder firing schedule array is not available. | 2020-09-17 |
20200291884 | Method and Device for Diagnosing a Crankcase Ventilation Line for an Internal Combustion Engine - Various embodiments include a method for diagnosing a crankcase ventilation line of a crankcase ventilation device for an internal combustion engine having a crankcase, an intake tract, and a compressor arranged in the intake tract for compressing the intake air comprising: diverting fresh air from the intake tract via a fresh air supply line; either enabling or inhibiting a flow of fresh air into a free volume of the crankcase depending on a switch position of a shut-off valve in the fresh air supply line; detecting a nitrogen oxide concentration in the crankcase during the process of crankcase ventilation, close to the point of introduction into the intake tract upstream of the compressor using a nitrogen oxide sensor; and evaluating the tightness of the crankcase ventilation line based at least in part on the detected nitrogen oxide concentration. | 2020-09-17 |
20200291885 | METHOD AND SYSTEM FOR FUEL INJECTOR BALANCING - Methods and systems are provided for reducing errors in estimated fuel rail pressure incurred at the time of a scheduled injection event due to engine-driven cyclic fuel rail pressure changes. In one example, a pulse-width commanded during a scheduled injection event is determined as a function fuel rail pressure samples collected over a moving window that is customized for the corresponding fuel injector. In another example, the commanded pulse-width is determined as a function of an average fuel rail pressure sampled during a quiet zone of injector operation and predicted fuel rail pressure altering events occurring between the quiet zone and the scheduled injection event. | 2020-09-17 |
20200291886 | METHOD AND SYSTEM FOR FUEL INJECTOR BALANCING - Methods and systems are provided for reducing errors in estimated fuel rail pressure incurred at the time of a scheduled injection event due to engine-driven cyclic fuel rail pressure changes. In one example, a pulse-width commanded during a scheduled injection event is determined as a function fuel rail pressure samples collected over a moving window that is customized for the corresponding fuel injector. In another example, the commanded pulse-width is determined as a function of an average fuel rail pressure sampled during a quiet zone of injector operation and predicted fuel rail pressure altering events occurring between the quiet zone and the scheduled injection event. | 2020-09-17 |
20200291887 | FUEL SUPPLY SYSTEM FOR ENGINE, FUEL INJECTION CONTROL DEVICE FOR ENGINE, AND FUEL SUPPLY METHOD FOR ENGINE - A fuel supply system includes an injector, an air flow meter, and an engine controller. The engine controller includes a fuel supply amount setting unit, a fuel cut controller, a fuel supply amount correcting unit, and an injector controller. The fuel supply amount setting unit sets a fuel supply amount on the basis of an intake air amount. The fuel cut controller executes and ends a fuel cut. The fuel supply amount correcting unit increases, on the basis of a reverse air amount, the fuel supply amount after the fuel cut in at least one cylinder, with respect to a basic supply amount corresponding to the intake air amount. An amount of the increase is greater at an initial fuel supply than in fuel supply at a second time and onward. The injector controller outputs, to the injector, a signal corresponding to the increased fuel supply amount. | 2020-09-17 |
20200291888 | ACTUATOR DEVICE UTILIZING RADIATIVE COOLING - An actuator device includes a housing that defines an enclosed volume region, the housing comprising a movable surface such that at least a portion of the housing is expandable between an expanded state to a contracted state, and the enclosed volume region having a characteristic dimension that is defined as a cube root of an average of a volume of the enclosed volume region in the expanded state and in the contracted state, a working fluid within the enclosed volumetric region, the working fluid comprising a substantially transparent compressible fluid and electromagnetic (EM) radiation-absorbing solid elements distributed within the compressible fluid, wherein the solid elements have an absorptivity in a particular range of EM radiation wavelengths, a heating system for directing thermal energy into the working fluid at predetermined times, and wherein the housing includes an EM radiation transmitting portion having a sufficient area and a sufficient transparency such that more than 25% of the thermal energy directed into the working fluid by the heating means is radiative emitted through the EM radiation transmitting portion as black body EM radiation emitted by the solid elements of the working fluid. | 2020-09-17 |
20200291889 | ENGINE EXHAUST SKIN CONNECTION SYSTEM - A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing. | 2020-09-17 |
20200291890 | INTEGRATED TAIL CONE AND MOUNTED GENERATOR - A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing. | 2020-09-17 |
20200291891 | CORE AIR FLOW TO EQUALIZE TEMPERATURE DIFFERENTIAL - A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet. | 2020-09-17 |
20200291892 | BLOCKER DOOR ASSEMBLY HAVING A THERMOPLASTIC BLOCKER DOOR FOR USE IN A TURBINE ENGINE - A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material. | 2020-09-17 |
20200291893 | THRUST REVERSER CASCADE FOR AN AIRCRAFT NACELLE - A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions. | 2020-09-17 |
20200291894 | THRUST REVERSER FOR AN AIRCRAFT ENGINE NACELLE, COMPRISING A PANEL FOR AVOIDING A MOVABLE SLAT OF THE WING, AND NACELLE ASSOCIATED THEREWITH - A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position. | 2020-09-17 |
20200291895 | BEADED FINGER ATTACHMENT - A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket. | 2020-09-17 |
20200291896 | ACOUSTIC PANEL FOR AN AIRCRAFT TURBOJET NACELLE, AND METHOD FOR MANUFACTURING AN ELEMENT OF A NACELLE - An acoustic panel for an aircraft turbojet nacelle, of the type including an outer skin, an inner skin, and a cellular core which is interposed between the outer skin and the inner skin, includes a plurality of corrugated strips, each corrugated strip extending longitudinally in length while forming a succession of bosses and recesses, the corrugated strips arranged to delimit cells which extend globally perpendicularly to the skins. Each corrugated strip extends in width from a first end forming an outer folded edge, which bears on the outer skin, to a second end forming an inner folded edge, which bears on the inner skin. | 2020-09-17 |
20200291897 | OXIDIZER INJECTOR FOR MOTOR - An oxidizer injector for motor, which is mainly suitable for using in a combustion chamber, the oxidizer injector mainly comprises a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber. | 2020-09-17 |
20200291898 | AUXILIARY BOOSTER WITH OPTIMISED ARCHITECTURE - A solid propellant auxiliary booster intended to be attached to the main body of a launcher comprises a cylindrical body extending in a longitudinal direction between a rear face in communication with a nozzle and a front face formed by a conical structure connected to the cylindrical body of the booster. The cylindrical body delimits a first internal volume and the conical structure of the front face delimits a second internal volume. The auxiliary booster contains a solid propellant charge. The first internal volume of the cylindrical body communicates with the second internal volume of the conical structure. The solid propellant charge is present both in the first and second internal volumes. | 2020-09-17 |
20200291899 | HYBRID ROCKET ENGINE WITH IMPROVED SOLID FUEL SEGMENT - A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency. | 2020-09-17 |
20200291900 | CHARGE FORMING DEVICE WITH ADJUSTABLE VALVE LIMITER - In at least some implementations, a limiter cap assembly for a carburetor having a cavity in which one or more adjustable valves are received, includes a plug adapted to be received within a cavity of the carburetor and having an opening and a cavity aligned with the opening, a clasp engageable with the plug and having at least one retention feature and an opening aligned with the opening of the plug, and a limiter cap received within the opening of the plug and engaged with the retention feature of the clasp. Removal of the limiter cap from the plug opening is prevented by engagement of the retention feature with the limiter cap and by engagement of the clasp with the plug. | 2020-09-17 |
20200291901 | TOTAL RECYCLING SYSTEM OF CAPTURING, CONVERSION AND UTILIZATION OF FLUE GAS FROM FACTORY, POWER PLANT AND REFINERY - A total recycling system of capture, conversion and utilization of flue gas from factory, power plant and refinery. A combined decontamination and dust removal unit removes dust and oxides; a capture subsystem captures CO | 2020-09-17 |
20200291902 | PURGE SYSTEM FOR FUEL EVAPORATION GAS OF VEHICLE - A purge system for fuel evaporation gas may include an ejector, having a nozzle configured to allow driving fluid to pass therethrough, a driving inlet through which the driving fluid is supplied into the ejector, a suction inlet through which purge gas including a fuel component is drawn as suction fluid from a canister into the ejector, a diffuser outlet through which a mixture of the driving fluid that has passed through the nozzle and the drawn purge gas is discharged out of the ejector, and a suction passage extending from the suction inlet toward a downstream side of the nozzle based on a flow direction of the driving fluid, and a bypass passage coupled from the suction inlet to the driving inlet. | 2020-09-17 |
20200291903 | CANISTER - A canister includes a main chamber where a charge port and a purge port are located, and at least one subsidiary chamber. Any one of the at least one subsidiary chamber includes an atmosphere port. The at least one subsidiary chamber includes at least one specified subsidiary chamber including a specified absorption layer containing specified activated carbon. An L/D of the specified absorption layer is equal to or greater than 2.0 and equal to or less than 7.0 where L is a length of the specified absorption layer and D is an equivalent diameter of a cross-section of the specified absorption layer taken orthogonally to longitudinal directions. The specified activated carbon has BWC equal to or greater than 8.0 g/dL and equal to or less than 10.5 g/dL. | 2020-09-17 |
20200291904 | EVAPORATIVE FUEL VAPOR EMISSION CONTROL SYSTEMS - The present disclosure describes an evaporative emission control canister system that includes: one or more canisters comprising at least one vent-side particulate adsorbent volume comprising a particulate adsorbent having microscopic pores with a diameter of less than about 100 nm; macroscopic pores having a diameter of about 100-100,000 nm; and a ratio of a volume of the macroscopic pores to a volume of the microscopic pores that is greater than about 150%, and having a retentivity of about 1.0 g/dL or less. The system may further include a high butane working capacity adsorbent. The disclosure also describes a method for reducing emissions in an evaporative emission control system. | 2020-09-17 |
20200291905 | EXHAUST SYSTEM WITH EXHAUST GAS HEAT RECOVERY ASSEMBLY AND METHOD FOR OPERATION OF THE EXHAUST SYSTEM - An exhaust system with a first and a second exhaust conduit arranged in a parallel flow arrangement. The exhaust system further includes an exhaust gas heat recovery (EGHR) heat exchanger coupled to an exterior of the first exhaust conduit. The exhaust system further includes a first flow control valve controlling the flow of exhaust gas into the EGHR heat exchanger from the first exhaust conduit and a second flow control valve controlling the flow of exhaust gas through the second exhaust conduit. | 2020-09-17 |
20200291906 | METHOD AND APPARATUS FOR CONTROLLING AN INTERNAL COMBUSTION ENGINE - An engine includes an air intake system, an exhaust system, a single-cylinder-sourced EGR system, an exhaust sensor that is disposed to monitor exhaust gas from the single one of the cylinders, and a diverter valve. A controller includes an instruction set that executable to determine operation of the engine in a fuel cut-off mode, discontinue fuel flow to the single one of the cylinders, divert exhaust gas from the single one of the cylinders to the air intake system, determine an airflow, temperature, and an equivalence ratio of the diverted exhaust gas from the single one of the cylinders, determine a mass flowrate of oxygen in the diverted exhaust gas, integrate the mass flowrate of oxygen in the diverted exhaust gas, and discontinue the diverting of the exhaust gas from the single one of the cylinders when the integrated mass flowrate of oxygen is greater than a threshold value. | 2020-09-17 |
20200291907 | MULTI-MODAL MULTI-MEDIA AIR FILTRATION SYSTEM - The present invention relates to a multi-modal multi-media air filtration system which can include: a base having one or more connection features and a filter media assembly, the filter media assembly being configured to attach to the base at a first end and the cap at a second end. The filter media assembly also including a first filter media extending across a primary air flow path and a second filter media extending across a secondary air flow path. The air filtration assembly then includes a blocking mechanism and an actuation assembly being configured to work together so as to selectively open or close the secondary air flow path so as to alternate the degree of filtration passing through the filter media based on the degree of desired filtration. | 2020-09-17 |
20200291908 | SOUND ENHANCING SYSTEM - Methods and systems are provided for enhancing and delivering engine sounds to a vehicle cabin based on a selected mode. In one example, a method may include adjusting openings of one or more valves fluidically coupling one or more corresponding engine regions to a sound tube of a sound enhancing system based on the selected mode. Throttle opening may also be adjusted to compensate for air routed from the engine regions to the sound tube instead of flowing to the engine cylinders. | 2020-09-17 |
20200291909 | FLUID TANK FOR A POWER TOOL - A power tool includes a tool head having a working element and a powerhead configured to provide power to the working element. The powerhead includes a fluid tank configured to hold a combustible fuel and defines an initial internal volume having an internal pressure. A diaphragm is formed of a flexible material and forms at least a portion of the fluid tank. The diaphragm moves from an unexpanded state to an expanded state when a temperature of the combustible fuel increases above a threshold value. Movement of the diaphragm to the expanded state increases the internal volume of the fluid tank to allow the internal pressure of the fluid tank to remain approximately constant. | 2020-09-17 |
20200291910 | FUEL INJECTION VALVE - Provided is a fuel injection valve capable of quickly stopping a position of a movable element at a predetermined position after closing a valve while reducing an impact force of a valve body. Therefore, a valve body | 2020-09-17 |
20200291911 | A DEVICE FOR A COMMON RAIL FUEL INJECTION SYSTEM - The invention relates to a device ( | 2020-09-17 |
20200291912 | Starter Device, Pulley Assembly for a Starter Device, and Connecting Spring for a Pulley Assembly - A pulley assembly for a starter device for starting an internal combustion engine of a hand-guided power tool has a pulley with an axis of rotation extending in axial direction. A circumferential side of the pulley is positioned outwardly in radial direction relative to the axis of rotation. A circumferential recess is arranged at the circumferential side and accommodates a starter rope. The pulley is provided with a spring receptacle. A connecting spring is disposed in the spring receptacle and has a first end fixedly connected to the pulley. The spring receptacle and the recess overlap each other, viewed in the axial direction and viewed in the radial direction. A starter device is provided with the pulley assembly and a second end of the connecting spring is fixedly connected to a coupling device of the starter device that couples the pulley to the crankshaft of the combustion engine. | 2020-09-17 |
20200291913 | Auxiliary Heating System - An auxiliary heating system comprising interconnected piping which forms a closed fluid flow circuit for permitting a passage of coolant therein, and having formed chamber openings along a length thereof to receive at least one heating element which projects into the closed fluid flow circuit to be in direct contact with, and heat, the coolant. A pump is provided for circulating the coolant, along with a flow switch for monitoring flow of the coolant through the closed fluid flow circuit, wherein if the flow has ceased through the closed fluid flow circuit, the flow switch instructs the system to deactivate the heating elements. | 2020-09-17 |
20200291914 | Internal-Combustion-Engine Control Device and Internal-Combustion-Engine Control Method - Provided is a control device and a control method of a high-efficiency internal combustion engine capable of stabilizing combustion and suppressing NO | 2020-09-17 |
20200291915 | SYSTEM AND METHOD FOR ENGINE IGNITION COIL IDENTIFICATION - An ignition system for an internal combustion engine includes an ignition coil forming a part of a primary circuit and a secondary circuit, a power source to supply power to the ignition coil, and a controller to determine whether the ignition coil is a recognized ignition coil based on a measured risetime and a measured current level in the primary circuit, the measured current level being lower than that required to create a breakdown voltage of the ignition coil. | 2020-09-17 |
20200291916 | MULTI-STAGED COWL FOR A HYDROKINETIC TURBINE - The multi-staged cowl described herein allows to increase and maximize water mass flow and pressure drop at the runner cross-section of a hydrokinetic turbine so as to maximize produced power output, while respecting dimensional constraints provided by a shallow body of water, a river for example, in which the hydrokinetic turbine can be submerged. The multi-staged cowl described herein can thus be configured so as to allow water to flow through the hydrokinetic turbine at a substantially stable water mass flow, eliminating instability, avoiding vortices, minimizing cavitation and avoiding fluid separation to negligible levels, and can include an inlet, an outlet and multiple stages which can extend between the inlet and the outlet, so that water can flow therethrough in a water flow direction. | 2020-09-17 |
20200291917 | HYDROELECTRIC POWER SYSTEM - A hydroelectric power system can include: a first level including a drain system, the drain system including a bell siphon coupled to a mixed flow turbine and a cross flow turbine, the drain system configured to provide a path way for a working fluid to flow from the bell siphon, through the mixed flow turbine, and through the cross flow turbine; and a second level below the first level, the second level for receiving the working fluid from the cross flow turbine of the drain system of the first level. | 2020-09-17 |
20200291918 | INNER COVERING FOR WIND TURBINE BLADES AND METHOD FOR MOUNTING SAME - Inner covering for wind turbine blades and method for mounting same, wherein said covering consists of a wall cover with a flexible wall which is formed based on layers of composite materials, having shapes and dimensions being approximately the same as those of the inner area of the blade structural element, said cover being mounted on a support with which it is introduced inside the blade. Between the support and the cover, an inflatable chamber is arranged, which upon being inflated causes the cover to be compacted and adhered against the inner surface of the blade structural element. | 2020-09-17 |
20200291919 | VERTICAL AXIS TURBINE BLADE, TURBINE AND WIND POWER GENERATION DEVICE - A vertical axis wind turbine blade ( | 2020-09-17 |
20200291920 | High Yaw Error and Gust Ride Through - The present invention relates to a system adapted to reduce the load of a wind turbine in situations with high yaw error or by gust ride, which system has access to at least some operational parameters. The object is to reduce the maximal load of a wind turbine in situations where wind gust hits the wind turbine. The system can monitor at least a combination of these parameters, which system by a defined combination of at least some of actual parameters performs a pitch or speed regulation in order to bring the wind turbine into a safe mode of operation and reduce the load of the wind turbine. Hereby can be achieved that the system can monitor some of existing parameters for a wind turbine in operation and through these parameters it is possible with this system to perform an analysis of critical combinations of parameter values. In that way the system can react if a critical load exists because there is a critical combination of parameters and change the pitch of the blades towards the feathered position or by speed reduction. | 2020-09-17 |
20200291921 | FEEDFORWARD CONTROL METHOD AND DEVICE FOR WIND TURBINE SET IN WIND FARM - A feedforward control method for a wind turbine set in a wind farm, comprising: obtaining real-time operation data of a predetermined wind turbine set in a wind farm; inputting the acquired real-time operation data into a predetermined prediction model corresponding to the predetermined wind turbine set so as to acquire prediction data by means of the predetermined prediction model; according to the acquired prediction data, determining whether to start a feedforward control function for the predetermined wind turbine set so as to control the operation state of the predetermined wind turbine set on the basis of a predetermined manner of feedforward control. The method may control a wind turbine set in advance and is beneficial in the safe operation of wind turbine sets. The present invention also relates to a feedforward control device for a wind turbine set in a wind farm, a control system, a computer readable storage medium and a field group controller. | 2020-09-17 |
20200291922 | MODEL PREDICTIVE CONTROL IN LOCAL SYSTEMS - A main computing system maintains and optimizes a predictive control model for an energy system, wherein the main computing system receives state information for the energy system, optimizes the predictive control model, and generates control rules for control of the energy system. The one or more local computing systems, each have a local memory for storing control rules for controlling the associated local state. The main computing system receives local state information and updates control rules, wherein the updated control rules comprise a subset of the control rules generated by the main computing system selected to be appropriate to the local state information received at the main computing system. | 2020-09-17 |
20200291923 | Advanced Wind Energy Generator - Basically the Advanced Wind Energy Generator is a vertical wind mill with moveable doors. By closing the doors on apparatus moving with wind, it can harvest more wind energy. Same doors will open as soon as they travel against blowing wind which will minimize the drag. This system will make moveable door wind mill quite yet effective. | 2020-09-17 |
20200291924 | CONFIGURATION OF WIND TURBINE CONTROLLERS - The wind turbine comprises at least one controller arranged to control a function of the wind turbine, and a data storage unit arranged to store controller specific data for the at least one controller, where the data storage unit is associated with the at least one controller to enable communication of the controller specific data between the data storage unit and the at least one controller. The method comprises detecting a connection between a programming enabling key and a connection interface dependent on a presence of the programming enabling key in proximity of the connection interface, initiating a programming mode wherein a control unit is enabled to receive controller specific data or wind turbine specific data from which the controller specific data can be determined, and obtaining the controller specific data or the wind turbine specific data via a manual action or via a trusted data source. | 2020-09-17 |
20200291925 | LIGHTNING PROTECTION SYSTEM FOR A WIND TURBINE AND WIND TURBINE COMPRISING SUCH A LIGHTNING PROTECTION SYSTEM - Provided is a lightning protection system for a wind turbine, including a connection unit to be placed between a nacelle and at least one blade of the wind turbine for conducting lightning current and/or static energy from the at least one blade to the nacelle, the connection unit including a first end portion with at least one nacelle contacting element, a second end portion with at least one blade contacting element, at least one first support member supporting the at least one nacelle contacting element, at least one second support member supporting the at least one blade contacting element, a base portion located between the first support member and the second support member, and at least one shifting element mechanically connecting the first support member and/or the second support member slidably relative to the base portion for amending a length of the connection unit in an amending direction from the blade to the nacelle. | 2020-09-17 |
20200291926 | METHOD FOR PROVIDING A WIND TURBINE BLADE WITH LIGHTNING PROTECTION AND A WIND TURBINE BLADE - A method for providing a wind turbine blade with lightning protection, the method including the steps of: providing a lightning protection cover including a non-conductive medium and a conductive medium embedded in the non-conductive medium, providing a blade body, and attaching the lightning protection cover to the blade body. An effective lightning protection is thus provided. | 2020-09-17 |