Patents Issued in October 20, 2016
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Publication number: 20160305249Abstract: A rotating machine includes a hub portion, wherein the hub portion comprises a forward face and an aft face. The rotating machine further includes a cooling channel formed on either the forward face or the aft face and configured to direct cooling air to a location on the rotating machine, wherein the cooling channel extends from a radially inner location along said face to a radially outer location along said face, and wherein the cooling channel is configured as a recess formed into an outer surface of said face.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Lorenzo Crosatti, Jason Smoke
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Publication number: 20160305250Abstract: A blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profile body extends from a first leading edge to a first trailing edge with a first chord extending form the first leading edge to the first trailing edge and being perpendicular to the radial direction. A plurality of flow deflectors extend along either the pressure surface or the suction surface within the lift generating section of the blade. The plurality of flow deflectors define a second profile body extending between a second leading edge and a second trailing edge with a second chord extending between the second leading edge and the second trailing edge.Type: ApplicationFiled: June 27, 2016Publication date: October 20, 2016Inventors: Francisco J. Diez-Garias, Arturo Villegas Vaquero
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Publication number: 20160305251Abstract: A rotor for a gas turbine engine includes a hub having an outer periphery, a first plurality of blades arranged on the outer periphery of the hub, and a second plurality of blades arranged on the outer periphery of the hub. The first plurality of blades is made of a first material and has a first elastic modulus over density ratio. The first plurality of blades has a first natural frequency. The second plurality of blades is made of a second material and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented.Type: ApplicationFiled: April 20, 2015Publication date: October 20, 2016Inventor: Bruce FIELDING
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Publication number: 20160305252Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.Type: ApplicationFiled: December 8, 2014Publication date: October 20, 2016Inventors: Lane Thornton, Thomas N. Slavens
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Publication number: 20160305253Abstract: A turbine blade with a cooling arrangement is provided. The turbine blade includes at least one supply chamber and at least one impingement cavity. The supply chamber includes multiple impingement channels configured to direct a cooling fluid from within the supply chamber to the impingement cavity. The supply chamber also includes one or more collector channels such that the cooling fluid from the impingement cavity is directed to a collector cavity within the turbine blade.Type: ApplicationFiled: October 25, 2013Publication date: October 20, 2016Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Janos Szijarto, Esa Utriainen
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Publication number: 20160305254Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform and a platform cooling passage extending inside of the platform. The platform cooling passage includes an inlet disposed through a non-gas path surface of the platform and an outlet disposed through a mate face of the platform.Type: ApplicationFiled: November 17, 2014Publication date: October 20, 2016Inventors: Daniel A. SNYDER, Jeffrey S. BEATTIE
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Publication number: 20160305255Abstract: An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.Type: ApplicationFiled: November 19, 2014Publication date: October 20, 2016Inventors: Iuliana Cernatescu, Thomas J. Watson, James O. Hansen, David Ulrich Furrer, Randy P. Salva
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Publication number: 20160305256Abstract: A method of fabricating a part by selectively melting powder, the method comprising the following steps: depositing a first layer (12) of a first powder (2) having a first element as its main element; depositing, on the first layer, a second layer (15) of a second powder (22) having a second element as its main element, which second element is different from the first element; and moving a first energy beam (11), e.g. a laser beam or an electron beam, over the second layer (15), the energy delivered by the first beam serving to initiate an exothermic reaction between the first element and the second element, the energy given off by the exothermic reaction acting to locally melt together the first and second layers (12, 15).Type: ApplicationFiled: December 4, 2014Publication date: October 20, 2016Applicant: SNECMAInventors: Stephane KNITTEL, Pascal Fabrice BILHE
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Publication number: 20160305257Abstract: A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Christopher W. Strock
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Publication number: 20160305258Abstract: A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abraisive filler between about 50%-75% by volume of the abrasive coating.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Applicant: United Technologies CorporationInventor: Christopher W. Strock
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Publication number: 20160305259Abstract: A blade retention arrangement is disclosed for retaining a blade within a disk or wheel within a turbine. The blade retention arrangement includes a dovetail connected with the blade for insertion within a dovetail slot formed in a circumference of the disk or wheel. A first chamfer is formed on an axially front bottom edge of the dovetail and a first deformation of a axially front surface of the wheel presses against the first chamfer whereby a first radially outward force is exerted on the dovetail with respect to an axis of the wheel that presses the dovetail against a first centrifugal retention surface of the dovetail slot. A second chamfer may be formed on an axially back bottom edge of the dovetail that performs in the same manner. The first and second chambers may be formed on respective ones of a forward and aft spacer, or on a bottom spacer instead of being formed on the blade dovetail directly.Type: ApplicationFiled: April 12, 2016Publication date: October 20, 2016Inventors: Charles Evans, Andrew Narcus, Paul DiCristoforo, Karl Streb
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Publication number: 20160305260Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each include a root that fits within dovetail slots of the rotor disk to couple the blades to the rotor disk. A platform assembly is coupled to the rotor disk to surround the blades.Type: ApplicationFiled: February 29, 2016Publication date: October 20, 2016Inventor: Ted J. Freeman
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Publication number: 20160305261Abstract: An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, where the low pressure spool is operated at high electrical demand to supply compressed air to the high pressure compressor of the high pressure spool, and where turbine exhaust is used to drive a second electric generator from steam produced in a heat recovery steam generator. The high pressure spool includes a high pressure compressor with a inner compressed air flow path and an outer compressed air flow path in which a higher pressure supplies cooling to a turbine airfoil that is then discharged into a combustor of the engine.Type: ApplicationFiled: April 6, 2016Publication date: October 20, 2016Inventors: John A Orosa, Joseph D Brostmeyer
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Publication number: 20160305262Abstract: A turbine shroud segment is metal injection molded (MIM) about a low melting point material insert. The low melting point material is dissolved using heat during the heat treatment cycle required for the MIM material, thereby leaving internal cooling passages in the MIM shroud segment without extra manufacturing operation.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventors: ERIC DUROCHER, GUY LEFEBVRE
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Publication number: 20160305263Abstract: A coupling support member including a pair of divided pieces is placed in a coupling part between a vane base end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane base end portion from both the sides in the vane thickness direction. Linear protrusions are respectively formed on both the sides of the vane base end portion. Grooves engaged with the linear protrusions formed in the vane base end portion are respectively formed in the pair of divided pieces of the coupling support member. Side edges that are located on the vane center side of the pair of divided pieces and extend along the chord direction are formed so as to protrude toward the vane center, and the respective tip ends of the side edges are chamfered.Type: ApplicationFiled: June 28, 2016Publication date: October 20, 2016Applicant: IHI CorporationInventors: Hiroyuki YAGI, Rintarou Kajiwara
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Publication number: 20160305264Abstract: A seal component for a turbomachine includes a stator platform configured to be disposed on an end of a stator airfoil and a scoop disposed on a first edge of the stator platform configured to be oriented obliquely with respect the stator airfoil and configured for generating a region of high pressure static fluid flow adjacent the first edge of the stator platform.Type: ApplicationFiled: November 19, 2014Publication date: October 20, 2016Inventors: Jordan T. Wall, William W. Frank, Davis S. Jang
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Publication number: 20160305265Abstract: Shroud assemblies and shrouds for gas turbine engines are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a rib disposed between and in contact with the forward flange and the rear flange.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventor: David Scott STAPLETON
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Publication number: 20160305266Abstract: The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a rotary seal element, the rotary seal element configured to rotate during operation of a gas turbine engine, and a stationary seal element having an annular seal surface. The stationary seal element includes a first area of the annular seal surface configured to engage with the rotary seal element, and the stationary seal element includes a second area of the annular seal surface configured to provide reduced resistance to the rotary seal element during a flight windmilling event.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventors: Allison ZYWIAK, Graham R. PHILBRICK
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Publication number: 20160305267Abstract: An outer air seal includes a seal wall, a heat shield, a side wall and a blade seal disposed radially inward of the seal wall. The seal wall has axially opposed first and second ends. The heat shield is radially outward of the seal wall and has first and second ends axially opposed ends. The second end of the heat shield is joined to the second end of the seal wall. The side wall is between the seal wall and the heat shield and spaces the first ends of the heat shield and the seal wall apart to form an inner cavity therebetween. Inner and outer diameter ends of the side wall are joined to the first ends of the seal wall and of the heat shield, respectively. The heat shield is configured to thermally isolate an outer case from the inner cavity and the seal wall.Type: ApplicationFiled: November 11, 2014Publication date: October 20, 2016Inventor: Brian Ellis Clouse
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Publication number: 20160305268Abstract: A drive link for an active clearance control system of a gas turbine engine includes a puller damped with respect to an actuation cylinder.Type: ApplicationFiled: February 6, 2014Publication date: October 20, 2016Applicant: United Technologies CorporationInventor: Brian Duguay
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Publication number: 20160305269Abstract: An active clearance control system of a gas turbine engine includes a radially adjustable blade outer air seal system movable between a radially contracted Blade Outer Air Seal (BOAS) position that defines a first air volume and a radially expanded Blade Outer Air Seal (BOAS) position that defines a second air volume, the second air volume different than the first air volume. An accumulator system accommodate a difference in air volume between the first air volume and the second air volume.Type: ApplicationFiled: February 6, 2014Publication date: October 20, 2016Inventors: Ken F. BLANEY, Todd M. LA PIERRE
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Publication number: 20160305270Abstract: The off-shore gas turbine system comprises a floating structure with at least one deck and a baseplate mounted on the deck. The baseplate supports a gas turbine having: a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, an intermediate pressure turbine and a low pressure turbine. The low pressure compressor is driven into rotation by the intermediate pressure turbine and the high pressure compressor is driven by the high pressure turbine. The low pressure turbine has a load coupling. The system further comprises a driven equipment mechanically connected to the load coupling of the low pressure turbine and driven into rotation by the low pressure turbine. An intercooler is provided between the low pressure compressor and the high pressure compressor. The baseplate is supported on the deck separately from the intercooler.Type: ApplicationFiled: December 5, 2014Publication date: October 20, 2016Inventors: Daniele MARCUCCI, Massimo CARMIGNANI, Francesco CAPANNI, Ian Paul KAY, Paolo BIANCHI
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Publication number: 20160305271Abstract: One exemplary embodiment of this disclosure relates to an article having a multi-layer wall structure having an embedded sensor. Further, the multi-layer wall structure and the sensor are bonded together.Type: ApplicationFiled: November 14, 2014Publication date: October 20, 2016Applicant: United Technologies CorporationInventors: Wayde R. Schmidt, Slade R. Culp
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Publication number: 20160305272Abstract: This disclosure relates to a variable area nozzle of a gas turbine engine. The variable area nozzle includes, among other things, a control unit, a translatable structure, and a plurality of actuators configured to adjust the position of the translatable structure. The plurality of actuators are fluidly coupled to a common fluid source. The control unit is configured to provide instructions to at least one of the actuators to compensate for an asymmetric load from the translatable structure.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventor: Craig T. Stambaugh
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Publication number: 20160305273Abstract: Methods and systems are provided for determining a reference position associated with a variable geometry member. One exemplary method involves actuating the variable geometry member in a first direction with a first reference torque and obtaining a first position associated with the variable geometry member in response to the first reference torque. After actuating the variable geometry member with the first reference torque, the method continues by actuating the variable geometry member in the first direction with a second reference torque that is less than the first reference torque, obtaining a second position associated with the variable geometry member in response to the second reference torque, and identifying the second position as the hard-stop reference position when a difference between the first position and the second position is less than a fault threshold.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Todd Andrew Ratke, Miguel Angel Perez Leal
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Publication number: 20160305274Abstract: A variable turbine geometry turbocharger (100) with an adjustment ring assembly (45) having an adjustment ring (50) and a series of pivotable guide vanes (30) that are operably connected to the adjustment ring (50). A spring-biased retention clip (60) is between adjacent vane levers (36) and is attached to the adjustment ring (50). The retention clip (60) applies a force against the adjacent vane levers (36) and dampens and reduces movement of corresponding components.Type: ApplicationFiled: December 12, 2014Publication date: October 20, 2016Inventor: Donald Michael KENNEDY
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Publication number: 20160305275Abstract: Apparatuses are provided for a containment ring. The containment ring includes a first portion having a first ring composed of a first material with a first ductility. The containment ring also includes a second portion coupled to the first ring. The second portion is composed of a second material having a second ductility that is less than the first ductility and the first ductility is greater than about forty percent elongation.Type: ApplicationFiled: April 14, 2015Publication date: October 20, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Timothy Ertz, David T. Bailey, Reha Gomuc
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Publication number: 20160305276Abstract: A gas turbine with a burner, which gas turbine has at least one fuel feed line and at least one fuel outflow line, wherein a flushing water line is connected fluidically to the fuel feed line, and wherein a leakage oil tank is connected fluidically via a drainage line to the fuel outflow line and the connection of the fuel outflow line and the drainage line is provided at a point downstream of at least one closure valve in the fuel outflow line, wherein a bypass line is connected fluidically to the fuel outflow line upstream of the closure valve, which bypass line connects the fuel outflow line fluidically to the leakage oil tank.Type: ApplicationFiled: December 3, 2014Publication date: October 20, 2016Applicant: Siemens AktiengesellschaftInventors: Jürgen Meisl, James Smith
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Publication number: 20160305277Abstract: Nozzle used for spraying a liquid substance towards a compressor of a gas turbine engine, comprising an elongated body having an end for ejecting the liquid substance, a conduit for the liquid substance internal to the elongated body and extending up to the end, a recess located at the end, wherein the conduit ends in the recess; wherein the recess opens towards the lateral surface of the elongated body, typically a cylindrical body, and the conduit is tangential to the bottom of the recess.Type: ApplicationFiled: December 4, 2014Publication date: October 20, 2016Inventors: Mario Pecchioli, Celia Navarro-Canales, Jorge Omar Manon-Cantu, Tommaso Olivieri
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Publication number: 20160305278Abstract: A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventor: Matthew H. Lang
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Publication number: 20160305279Abstract: A heat transfer apparatus for a gas turbine engine includes: a component having a wall structure defining a flow bounding surface; a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventors: William Dwight GERSTLER, James Michael KOSTKA, Jeffrey Douglas RAMBO, John William MOORES
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Publication number: 20160305280Abstract: A steam power plant with a liquid/steam circuit includes a steam generator for converting a liquid into steam, a steam turbine and a condenser for converting the steam into the liquid, a generator and a liquid cooling system for the generator, wherein the liquid cooling system has a connection to the liquid/steam circuit via a bypass-like path of flow through which the liquid from the liquid/steam circuit can be branched out to the liquid cooling system and can be led back from the liquid cooling system to the liquid/steam circuit.Type: ApplicationFiled: September 18, 2014Publication date: October 20, 2016Applicant: Siemens AktiengesellschaftInventors: Esteban Grau Sorarrain, Christian Jäkel, Mario Koebe, Matthias Kowalski, Christoph Lehmann, Andrey Mashkin, Olga Plotnikova, Carolin Schild
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Publication number: 20160305281Abstract: A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine. The casing assembly includes an inner casing portion defining a casing volume VC and a counter-flow cooling system arranged within the inner casing portion. The counter-flow cooling system includes a plurality of ducts that collectively define a channel volume Vch. The plurality of ducts is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction. The casing volume and the channel volume define a volume ratio of about 0.0002<VCh/VC<0.9.Type: ApplicationFiled: June 7, 2016Publication date: October 20, 2016Inventors: Henry Grady Ballard, JR., Kenneth Damon Black, John David Memmer
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Publication number: 20160305282Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.Type: ApplicationFiled: June 29, 2016Publication date: October 20, 2016Applicant: United Technologies CorporationInventors: Fred NguyenLoc, San Quach
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Publication number: 20160305283Abstract: A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing (8) rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.Type: ApplicationFiled: April 15, 2016Publication date: October 20, 2016Applicant: SNECMAInventors: Serge Rene MORREALE, Dominik IGEL
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Publication number: 20160305284Abstract: A lubrication system for an engine including a scavenge pump configured to provide lubricant to the engine during a normal condition, an auxiliary pump configured to provide lubricant to the engine during an abnormal condition, a pressure sensor disposed at an outlet of the auxiliary pump for detecting a pressure created by the auxiliary pump, and a restriction device disposed in a conduit fluidly connecting the scavenge pump to the outlet of the auxiliary pump and configured to increase a first pressure produced by the auxiliary pump at the pressure sensor, wherein the first pressure is greater than a second pressure created by the scavenge pump at the pressure sensor.Type: ApplicationFiled: December 2, 2014Publication date: October 20, 2016Inventors: Jacob P. Mastro, Francis Parnin
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Publication number: 20160305285Abstract: An annular casing for a rotor of a gas turbine engine includes a casing treatment having at least one groove defined in the annular casing wall with an open end defined in an inner surface of the annular casing wall, and a perforated sheet overlapping the open end of the at least one groove. The perforated sheet includes a plurality of apertures therethrough in fluid communication with the at least one groove. A method of reducing flow losses through a flow path having a rotor with a plurality of rotating blades extending therethrough is also presented.Type: ApplicationFiled: April 14, 2015Publication date: October 20, 2016Inventors: Tibor URAC, Peter TOWNSEND, Ignatius THERATIL
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Publication number: 20160305286Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.Type: ApplicationFiled: April 20, 2015Publication date: October 20, 2016Inventors: Bryce Loring Heitman, Michael Todd Radwanski, Darrell Glenn Senile
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Publication number: 20160305287Abstract: A pin insertion hole penetrating an outer member from an outer circumferential side to an inner circumferential side is formed in the outer member. A pin groove that is concave from an outer circumferential side to an inner circumferential side is formed in an inner member. A positioning device includes a pin that is inserted into the pin insertion hole of the outer member and the pin groove of the inner member, a liner holder that comes in contact with a groove side surface of the pin groove, and a liner that is disposed between the liner holder and the pin in the pin groove.Type: ApplicationFiled: December 17, 2014Publication date: October 20, 2016Inventors: Shinya HONDA, Akihiko SHIROTA
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Publication number: 20160305288Abstract: A system includes a probe. The probe includes a sensing component configured to sense a parameter of a turbomachine. The probe also includes an inlet configured to receive a cooling inflow. The probe also includes a cooling passage configured to receive the cooling inflow from the inlet. The cooling passage is disposed along at least a portion of the probe, and the cooling inflow absorbs heat from the probe. The probe also includes an outlet coupled to the cooling passage and configured to receive an outflow from the cooling passage. The outflow includes at least a portion of the cooling inflow. The system also includes an ejector coupled to the outlet.Type: ApplicationFiled: March 3, 2016Publication date: October 20, 2016Inventor: Srinivas Pakkala
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Publication number: 20160305289Abstract: Disclosed herein is a hybrid power generation system using a supercritical CO2 cycle, which includes a first working fluid circuit configured to produce electric power by a first working fluid heated in a boiler, and a second working fluid circuit configured to produce electric power by a second working fluid, and the first and second working fluid circuits share the boiler. The hybrid power generation system can remove an air preheater of a thermal power generation system and separate heat exchange units for exhaust gas and air after combustion, so as to utilize the heat exchange units as a heat source and a cooling source in a supercritical CO2 cycle. Consequently, it is possible to improve power generation efficiency by recovering the leakage loss of the air preheater.Type: ApplicationFiled: March 18, 2016Publication date: October 20, 2016Applicant: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.Inventor: Jeong Ho HWANG
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Publication number: 20160305290Abstract: The invention concerns a cam follower including a tappet having a cylindrical outer surface centered on a longitudinal axis (Y1) and adapted to slide in a housing surrounding the tappet, a pin extending between two opposite ends along a transverse axis (X1) perpendicular to the longitudinal axis (Y1), a roller element movable in rotation relative to the pin around the transverse axis (X1) and adapted to roll on a cam, and an antirotation member for preventing a rotation of the tappet around the longitudinal axis (Y1) in the housing. According to the invention, the antirotation member is one of overmoulded onto the tappet and the tappet is overmolded onto the antirotation member. The invention also concerns an injection pump for a motor vehicle, each having a cam follower. The invention also concerns a method for manufacturing a cam follower.Type: ApplicationFiled: April 14, 2016Publication date: October 20, 2016Applicant: Aktiebolaget SKFInventors: Jouanno Guillaume, Nicolas Berruet, François Champalou, Benoît Hauvespre, Samuel Viault
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Publication number: 20160305291Abstract: A multipart rotor (1) for a hydraulic camshaft adjuster (2) is provided, the multipart rotor having a rotor main body (3) which, together with a first rotor secondary body (4), forms hydraulic means-conducting channels (9) oriented in a radial direction, the first rotor secondary body (4) being arranged radially within the rotor main body (3).Type: ApplicationFiled: October 22, 2014Publication date: October 20, 2016Applicant: Schaeffler Technologies AG & Co. KGInventor: Juergen Weber
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Publication number: 20160305292Abstract: A multi-part rotor (1) for a hydraulic camshaft adjuster, including two partial rotor members (2) which rest against each other along a separation plane (3) extending perpendicular to the axial direction and which jointly define hydraulic medium ducts (4) extending within said separation plane (3) and, including an additional rotor member (5) that conducts hydraulic medium from opposite axial directions in a targeted manner to different hydraulic medium ducts (4). The additional rotor member (5) or at least one positively engaging anti-twist element (6) is secured to one or both partial rotor members (2) for conjoint rotation therewith.Type: ApplicationFiled: October 22, 2014Publication date: October 20, 2016Inventors: Juergen Weber, Christian Boesel
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Publication number: 20160305293Abstract: A compression-release brake system for effectuating a compression-release engine braking operation in connection with an internal combustion engine. The system includes a lost motion exhaust rocker assembly including a rocker arm, an actuation piston slidably received by the rocker arm to define part of a piston cavity in the rocker arm and movable between a piston retracted position and a piston extended position, the actuation piston configured to operatively associate with the exhaust valve to permit unseating of the exhaust valve from the seated state, and a reset device received by the rocker arm and operatively associated with the actuation piston to return the exhaust valve to the seated state by the end of the expansion stroke in the brake-on mode.Type: ApplicationFiled: June 27, 2016Publication date: October 20, 2016Inventors: Vincent MENEELY, Robert Price
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Publication number: 20160305294Abstract: A hybrid vehicle includes a hybrid module, a transmission and a torque converter. The lubrication system associated with the torque converter includes an oil sump within the torque converter housing which is intended to be managed as a “dry” sump oil lubrication system. There is an oil pump in communication with the sump in order to manage the sump oil level. By monitoring an operational parameter of the oil pump motor (pressure, torque, or current) oil aeration can be detected.Type: ApplicationFiled: June 28, 2016Publication date: October 20, 2016Inventors: Charles F. Long, Thomas A. Wright
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Publication number: 20160305295Abstract: Apparatuses are disclosed for machine fluid monitoring /sampling comprising a transparent sight glass attachable to a machine such that machine fluid is transferable to the sight glass. The sight glass may have an open first end, a closed second end, a sidewall, and an inside surface and an outside surface extending from the open first end to the closed second end and at least partially surrounding a cavity for the machine fluid, and one or more remote sensing ports. The one or more remote sensing ports may have a wall, an inner face, and an outer face, and may be positioned between the open first end and the closed second end of the sight glass. The material of the one or more remote sensing ports may be shaped to reduce distortion and/or increase visibility of the machine fluid relative to portions of the sight glass bordering the remote sensing ports.Type: ApplicationFiled: April 18, 2016Publication date: October 20, 2016Inventors: James Chester Fitch, Thomas Chester Fitch, Michael Anthony Ramsey
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Publication number: 20160305296Abstract: An exhaust purification device for purifying exhaust gas flowing in an exhaust gas flow passage of an engine includes: a cylindrical casing; a pipe that is disposed on a downstream side of the casing and inserted in the casing so as to extend in a direction substantially orthogonal to an axial direction of the casing, the pipe being provided with a through-hole communicating with the casing; and an injector configured to inject a reducing agent from an upstream end of the pipe into the pipe, in which a contracting flow passage portion narrowing in an axial direction of the pipe from an upstream side toward the downstream side is formed in the exhaust gas flow passage in the casing.Type: ApplicationFiled: December 17, 2014Publication date: October 20, 2016Applicant: HINO MOTORS, LTD.Inventors: Kuniharu TOBE, Hirofumi TONGU, Tomoyuki TSURUTA
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Publication number: 20160305297Abstract: A sensor probe for an exhaust system including a sensor body, a sensor cup, and a fluid shield. The sensor body defines a conduit and having a plurality of apertures formed through a sidewall of the sensor body. The sensor cup is coupled to an end of the conduit of the sensor body and is in fluid communication with the conduit. The sensor cup includes an outlet formed therein. The fluid shield may be integrally coupled to the sensor cup and positioned relative to the outlet formed in the sensor cup such that the fluid shield deflects fluid away from the outlet.Type: ApplicationFiled: December 9, 2014Publication date: October 20, 2016Applicant: Cummins Emission Solutions, Inc.Inventors: Aashish Wadke, Snehal Khisty, Jim Alonzo, Elizabeth Balke
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Publication number: 20160305298Abstract: The invention relates to a metering device (10) for introducing a process liquid or auxiliary agent into a flow pipe of an internal combustion engine, in particular for introducing a reducing agent into an exhaust gas pipe (12). Said device comprises an injection valve (22) and a receiving device (50) comprising a heat sink element (46) and a cover element (48). The injection valve (22) and the receiving device (50) are combined to form a structural unit by means of bonded connections (62, 64).Type: ApplicationFiled: October 2, 2014Publication date: October 20, 2016Inventors: Martin Murst, Achim Knittel, Thilo Kreher, Thorsten Rankel, Jochen Winkler, Claudius Henkel, Gellert Elsoe
