Abstract: A vane assembly may comprise a plurality of airfoils each extending between an inner platform and an outer platform, the plurality of airfoils comprising a nominal airfoil, a thickened airfoil, and a first thinned airfoil circumferentially adjacent to the thickened airfoil, wherein, the nominal airfoil has a first chord thickness, the thickened airfoil has a second chord thickness, and the thinned airfoil has a third chord thickness, wherein the second chord thickness is greater than the first chord thickness and the third chord thickness is less than the first chord thickness, and a member disposed within the thickened airfoil.

Abstract: A vane includes an airfoil that defines a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil includes a truss structure that has ribs that define there between a plurality of through-cavities from the pressure side to the suction side. Honeycomb cells are disposed in the cavities. A face sheet defines at least one of the pressure side or the suction side. The face sheet has perforations that correspond in location to the honeycomb cells.

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

Abstract: A cooling assembly comprises a cooling cavity disposed inside of a turbine assembly. The cooling cavity is configured to direct cooling air inside a body of the turbine assembly. The cooling assembly comprises a cross-bank fluidly coupled with the cooling cavity and positioned to direct at least some of the cooling air out of the cooling cavity and outside of the body. The cross-bank comprises plural pins having first ends coupled with a first side interior surface of the body and opposite second ends coupled with a second side interior surface of the body. The cross-bank also includes a cross-bar connecting the pins. The cross-bar extends between the pins such that the cross-bar has a first end coupled with an exterior surface of a first pin of the pins and an opposite second end coupled with an exterior surface of a second pin of the pins.

Abstract: Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.

Abstract: A turbine blade includes a blade body including a top plate at a tip portion which is outside of a turbine rotor in a radial direction of the turbine blade and has an outer surface configured to face an inner circumferential surface of a casing, and a tip thinning which protrudes radially outward in the radial direction of the turbine blade from the outer surface of the top plate and extends from a leading edge side of the blade body to a trailing edge side of the blade body. A protrusion amount of the tip thinning based on the outer surface of the top plate is 0.25 times or more and 2.00 times or less a diameter of a discharge port of a cooling hole which passes through the top plate.

Abstract: Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, a radially outer shroud, and an airfoil extending between the blade root and the shroud. It is provided that the outer shroud have only a single sealing element, which projects radially from the shroud, in particular only a single sealing fin.

Abstract: An airfoil of an axial flow machine includes an airfoil part that has a suction surface and a pressure surface, an endwall as a shroud or a platform, and a fillet that is provided along a connecting portion between the airfoil part and the endwall. The fillet includes a first curved surface formed at least on a leading edge side and a trailing edge side in the airfoil part on the suction surface side and a second curved surface formed in a portion other than a portion where the first curved surface is formed. The second curved surface has a smaller curvature radius than the first curved surface.

Abstract: One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.

Abstract: The invention relates to a rectifier (1) for an aircraft turbomachine compressor, the rectifier comprising an inner ferrule (24), an outer ferrule (26), and stator blades (28) secured to the inner and outer ferrules, the rectifier also comprising a flange (34) secured to a downstream end of the outer ferrule (26) and designed to be fixed to a compressor housing (36), the flange being provided with air extraction openings (50) arranged at a distance from each other in a peripheral direction (52). According to the invention, at least one of the air extraction openings (50) has a stretched form in the peripheral direction (52).

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.

Abstract: A fixed vane turbocharger includes: an impeller; a housing including, inside thereof, an impeller housing space which accommodates the impeller, a scroll flow passage formed on a radially outer side of the impeller, and a communication flow passage which brings the impeller housing space and the scroll flow passage into communication; and at least one fixed vane unit disposed in the communication flow passage and fixed to a portion of the housing on an inner side of the scroll flow passage with respect to a radial direction of the impeller. Each of the at least one fixed vane unit includes at least two vane portions and a coupling portion coupling the two vane portions, and is formed of a single sheet metal member.

Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

Abstract: A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.

Abstract: An aircraft gas turbine engine (10) comprises a main engine spool (22) and a bearing arrangement (36) configured to rotatably support the main engine spool (22). The bearing arrangement (36) includes a damper (41) comprising a static element (42) and a moveable element (39). The gas turbine engine further comprises an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine spool (22), and the stator (32) is mounted to the moveable element (39) of the damper to be moveable with the moveable element (39).

Abstract: An aircraft gas turbine engine (10) comprises a main engine shaft (22) arranged to couple a turbine (17) and a compressor (13), the main engine shaft (22) defining an axial direction (9). The gas turbine engine (10) further comprises at least one radially extending offtake shaft (27) coupled to the main engine shaft (22), and a radially extending electric machine (25a, 25b) coupled to the radially extending offtake shaft (22).

Abstract: A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.

Abstract: A gas turbine engine includes a compressor section. A diffuser case is downstream of the compressor section. There is a combustor and a turbine section. A bearing compartment is inward of the combustor. A shaft connects the turbine section to the compressor section. The bearing compartment includes a bearing that supports the shaft. A plurality of tubes extend to the bearing compartment. Each of the plurality of tubes have a heat shield that includes a first half and a second half crimped together along lateral edges.

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.

Abstract: A gas turbine engine includes an engine static structure. A rotating structure is configured to rotate relative to the engine static structure. The rotating structure has a target area with first and second directions. The first direction is greater than the second direction. A lubrication system includes a nozzle having a non-circular exit aimed at the target area. The exit provides a width and a height. The width is greater than the height. The width is oriented in the first direction.

Abstract: The gas turbine engine can have an accessory gearbox having a sump; an oil tank; a user interface configured to generate a signal upon receiving a user input indicative of an oil measurement reading; and a pump configured to pump oil from the sump to the oil tank upon receiving the user input.

Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.

Abstract: The invention relates to a machine for converting heat into mechanical energy comprising an expansion device producing mechanical energy from a flow of vapor of a fluid; an evaporator heated by a heat source to a high temperature and configured to supply the expansion device with vapor; a condenser cooled by a heat sink to a low temperature and configured to condense the vapor discharged by the expansion device; a liquid circuit configured to transfer fluid in liquid phase from the condenser to the evaporator; a vapor circuit configured to transfer fluid in vapor phase from the evaporator to the condenser; and valves configured to, in a first, active stroke, close the liquid and vapor circuits, and, in a second, inactive stroke, open the liquid and vapor circuits.

Abstract: An electrically-actuated variable camshaft timing (VCT) phaser is employed for use with an internal combustion engine (ICE). The electrically-actuated VCT phaser includes a gear set assembly and a fixture. The gear set assembly has an input gear and an output gear, among other possible components. The input gear receives rotational drive input from an engine crankshaft, and the output gear transmits rotational drive output to an engine camshaft. The fixture is secured in the gear set assembly. Amid installation of the electrically-actuated VCT phaser on the ICE, the fixture constrains rotational movement of the gear set assembly. After installation, the fixture can be removed from the gear set assembly.

Abstract: A compact, modular, lost motion variable valve actuation assembly includes a dry start hydraulic circuit to enable quick priming of a lost motion master-slave circuit from a dry start reservoir to the master piston chamber during engine start. Motion of the master piston on engine startup may draw in fluid from the dry start hydraulic circuit. The dry start components may be integrated into a compact modular rocker shaft pedestal package suitable for retrofit on existing engine head assemblies. The master piston may include a push tube interface that includes a deep push tube cavity and lubrication capabilities in the master piston that provides for improved wear, stability, easy installation and alignment. The slave piston may be provided with a valve catch to reduce valve closing velocity during cycles involving lost-motion.

Abstract: An engine oil filler cap for monitoring an internal combustion engine comprises: a processor; and a sensor module comprising a pressure sensor configured to sense crankcase pressure of the internal combustion engine and to output data representative of the sensed crankcase pressure to the processor. The engine oil filler cap is configured to provide a housing for the processor. The processor is configured to determine a value representative of the firing frequency of the internal combustion engine based on the output data.

Abstract: A heating disk for heating up a stream of exhaust gas and/or a component for exhaust gas aftertreatment has a honeycomb body, wound from a plurality of smooth and corrugated metal layers stacked on top of one another. The honeycomb body is received within a carrier shell and an electrical contact is fed through the carrier shell. The honeycomb body is connected to a current source via the electrical contact. The electrical contact has a contact strip within the carrier shell extending in the circumferential direction of the carrier shell. An insulating region is formed between the carrier shell and the contact strip. A plurality of stacks of layers are electrically insulated from one another. Each of the stacks of layers are formed from the plurality of smooth and corrugated metal layers, and which are arranged directly adjacent to one another and conductively connected to the contact strip.

Abstract: An aftertreatment component includes an aftertreatment housing. The aftertreatment housing has a first surface positioned so as to be directly impinged by diesel exhaust fluid injected into the aftertreatment housing. The first surface is a polished surface.

Abstract: The present invention relates to a method for producing automobile exhaust gas catalytic converters, to the catalytic converters as such and to the use thereof. In particular, the method comprises a step which results, independently of the actual drying process, in the catalytically active material used being dried. The invention is especially used in the coating of wall-flow filters.

Abstract: An exhaust system provided to an engine having an output shaft extending in a specific direction, includes an exhaust passage, a turbocharger having a turbine housing, and purifying parts. The exhaust passage includes a first passage part extending to one side in the specific direction from the turbine housing, a third passage part extending in the specific direction below the turbine housing, and a second passage part extending upward from one end part of the third passage part in the specific direction. A center axis of the second passage part inclines so that an upper end thereof is located on one side of a lower end in the specific direction. The first passage part has in an upper surface thereof an inclined part to which one of a sensor configured to detect a property of exhaust gas and an injector configured to inject fluid into exhaust gas, is attached.

Abstract: An adaptive urea mixer comprises a housing (1) and a first movable plate (2), a second movable plate (3), and a first fixed ring (4) sequentially provided in a direction from an air inlet to an air outlet in the housing. The first fixed ring (4) is fixedly connected to an inner side wall of the housing (1). A plurality of guide columns (9) are provided on the first fixed ring (4). A first position-limiting portion and a second position-limiting portion are provided on the guide column (9). The first movable plate and the second movable plate are sleeved on the guide column (9). A first elastic support element (12) is sleeved on the guide column (9) between the second position-limiting portion (11) and the first movable plate (2), and a second elastic support element (13) is sleeved on the guide column (9) between the first fixed ring (4) and the second movable plate (3). Both a first flow guide plate and a second flow guide plate are fixedly connected to the first fixed ring (4).

Abstract: A vehicle exhaust system includes an injector assembly having an injector mount configured to mount an injector to an exhaust component. The injector mount includes a spray opening surrounding a spray axis. An injector housing extends from an inlet end that receives exhaust gases to an outlet end. The inlet end defines a planar area that is transverse to the spray axis. A spray protector extends axially from the injector mount to break the planar area. A vehicle exhaust component assembly comprising a mixer with the injector assembly and a method for injecting a fluid into an exhaust component using the injector assembly are also disclosed.

Abstract: In one aspect, an aspiration system for a work vehicle includes an exhaust tube extending along a flow direction from an upstream end to a downstream end. The exhaust tube defines an exhaust passage extending from the upstream end of the exhaust tube to the downstream end of the exhaust tube. The exhaust tube includes a venturi portion. The aspiration system also includes an aspiration tube in flow communication with the venturi portion and configured to receive an aspirated airflow. The system further includes a flow adjustment mechanism provided in operative association with venturi portion such that the flow adjustment mechanism is configured to adjust a cross-sectional flow area of the venturi portion of the exhaust tube.

Abstract: Failure detection apparatus for a particulate filter includes: a sensor having a particulate matter detection unit that outputs a signal corresponding to the amount of accumulated PM, and a heater unit that heats the particulate matter detection unit; a regeneration control unit that causes the heater unit to heat the particulate matter detection unit to a regeneration temperature allowing the particulate matter to be burned off; a start detection unit that determines the start of the internal combustion engine; failure determination unit that determines whether exhaust gas contains water droplets while the engine is in operation; a heating control unit that causes the heater unit to heat the particulate matter detection unit to a first temperature allowing the accumulated particulate matter to remain and the moisture included in the particulate matter to be removed; and failure determination unit that determines whether the filter has failure based on a sensor output value.

Abstract: Systems for and methods of evacuating air from a muffler while it is being filled with a fibrous material are disclosed.

Abstract: A reservoir tank with an integrated ejector, includes: a tank body having a space in which a coolant and a gas are contained; and an ejector integrally coupled to the tank body, wherein the ejector is configured to cool the gas produced from a gas source using the coolant contained in the tank body before the gas flows into the tank body.

Abstract: Methods and systems are provided for operating a cylinder of an engine including a pre-chamber system. In one example, a method includes flowing gases from a pre-chamber to a cylinder of an engine prior to fueling the cylinder during a combustion cycle, adjusting a composition of the gases by adjusting at least one of an air injection amount to the pre-chamber and a fuel injection amount to the pre-chamber, and igniting an air-fuel mixture in the cylinder via a pre-chamber ignition event, the air-fuel mixture in the cylinder including the gas from the pre-chamber. In this way, combustion qualities in the cylinder may be adjusted in order to increase a performance and/or an efficiency of the cylinder.

Abstract: A machine system includes a compressor, and a cooler having an inlet tank to receive compressed air from the compressor, and a header assembly attached to the inlet tank and including a plurality of cooling tubes supported in the header and each having an external heat exchange surface exposed to a flow of cooling air. The cooler further includes a plurality of graphite pack seals each extending peripherally around one of the cooling tubes, and a clamping assembly clamping the pack seals against the header to squeeze the pack seals into sealing contact with the cooling tubes and the header.

Abstract: A split-cycle engine includes: a first cylinder housing a first piston, wherein the first piston performs an intake stroke and a compression stroke, but does not perform an exhaust stroke; a second cylinder housing a second piston, wherein the second piston performs an expansion stroke and an exhaust stroke, but does not perform an intake stroke; and a valve chamber housing a valve, the valve comprising an internal chamber that selectively fluidly couples to the first and second cylinders, wherein the valve and internal chamber move within the valve chamber and relative to the first and second cylinders.

Abstract: A compressor arrangement for an internal combustion engine, including a compressor which is located in a compressor housing and has a low pressure side and a high pressure side, and includes a vacuum supply device which has: a propellant channel which has a nozzle and is fluidically connected on one side via a propellant inlet connection to the high pressure side of the compressor and on the other side via a propellant outlet connection to the low pressure side of the compressor; and a vacuum channel opening into the propellant channel fluidically between the propellant inlet connection and the propellant outlet connection.

Abstract: An internal combustion engine includes a crankcase and a cylinder head. The cylinder head and the crankcase delimit at least one cylinder in which a translationally moving piston is arranged. A water injection device injects water into the at least one cylinder. A crankcase ventilation device is fluidically connected to the crankcase. A blow-by mixture containing injection water can flow through the crankcase ventilation device. The crankcase ventilation device has an activated charcoal filter. The blow-by mixture containing the injection water can flow through the activated charcoal filter.

Abstract: A frameless cooling module includes a first and a second shroud panel arranged at opposing sides of the module and extending from the front of the module to the back of the module. At least one L-shaped stiffener bracket extends between the panels at an intermediate location along both the height direction and the depth direction of the module. One or more heat exchangers is arranged within the cooling module between the L-shaped stiffener bracket and the front of the module, and is at least partially secured within the cooling module by being mounted to the L-shaped stiffener bracket.

Abstract: A coolant diverter system and method of controlling coolant flow are provided. The coolant diverter system includes a coolant diverter body having a coolant inlet opening, a driveline retarder outlet opening and a bypass outlet opening. The coolant diverter system also includes a valve positioned in the coolant diverter body. The valve is configured in a first valve orientation to fluidly couple the coolant inlet opening to the driveline retarder outlet opening in isolation from the bypass outlet opening. The valve is configured in a second valve orientation to fluidly couple the coolant inlet opening to the driveline retarder outlet opening and the bypass outlet opening. The coolant diverter system also includes a valve controller configured to place the valve in the first valve orientation in response to activation of a driveline retarder coupled to the driveline retarder outlet opening for braking.

Abstract: An exhaust system includes an exhaust manifold structured to be fluidly coupled to an engine. A turbocharger including a turbine housing is fluidly coupled to the exhaust manifold. An exhaust pulse converter includes a first portion integral to the exhaust manifold and a second portion integral to the turbine housing. The exhaust pulse converter is structured to reduce engine pumping losses by reducing cross-talk of exhaust blowdown events from the engine.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: A heat management system for a turbomachine may include a first heat exchanger configured and arranged to receive a first fluid stream from a first duct, a second heat exchanger configured and arranged to receive the first fluid stream after discharging from the first heat exchanger, and a second duct fluidly communicating with the first duct between the first heat exchanger and the second heat exchanger to introduce a second fluid stream from the second duct to the first duct. A method of cooling fluid streams may include directing a first fluid stream from a first duct across or through a first heat exchanger, directing the first fluid stream across or through a second heat exchanger after discharging from the first heat exchanger, and directing a second fluid stream from a second duct to the first duct, with the second duct fluidly communicating with the first duct between the first heat exchanger and the second heat exchanger.

Abstract: In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between ?70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).

Abstract: The present application provides a variable frequency Helmholtz damper system for use with a combustor of a gas turbine engine. The variable frequency Helmholtz damper system may include one or more Helmholtz dampers and a purge medium temperature control unit for providing a flow of purge medium to the Helmholtz dampers. The purge medium temperature control unit may be in communication with a temperature control fluid flow such that the purge medium temperature control unit may vary the temperature of the flow of purge medium.

Abstract: A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

Abstract: A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.