Patents Issued in June 11, 2019
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Patent number: 10316663Abstract: A reinforced lightweight mine door for installation in a mine passageway. The mine door includes a generally rectangular sheet metal door panel having four sides and four corners, and a reinforcing structure projecting from a face of the door panel. The reinforcing structure has a central section and a plurality of channel sections extending from the central section toward respective sides or corners of the door panel. A mine door including at least one hinge arrangement having unique reversibility features is also disclosed.Type: GrantFiled: October 12, 2016Date of Patent: June 11, 2019Assignee: Jack Kennedy Metal Products & Buildings, Inc.Inventors: William R. Kennedy, John M. Kennedy
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Patent number: 10316664Abstract: An exhaust gas turbocharger may include a turbine housing and a turbine arranged in the turbine housing. The turbine housing may include at least two exhaust gas channels and a partition separating the at least two exhaust gas channels from one another. A wastegate valve may be arranged such that the at least two exhaust gas channels are connectable to a bypass duct bypassing the turbine. The wastegate valve may include a valve body and a valve seat interacting with the valve body. The wastegate valve may be configured such that at least one of a ram supercharging operation and a pulse supercharging operation is activated depending on a degree of opening of the wastegate valve.Type: GrantFiled: May 17, 2016Date of Patent: June 11, 2019Assignee: BMTS Technology GmbH & Co. KGInventors: Dirk Lummer, Martin Kropp
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Patent number: 10316665Abstract: A shaft coupling between a first shaft and a second shaft includes a seal assembly to minimize leakage. The seal assembly includes a ring press fit against an inner surface of the first shaft and a clearance fit with an inner surface of the second shaft. A seal is supported between the ring and the inner surface of the second shaft.Type: GrantFiled: March 10, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventor: Scott D. Virkler
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Patent number: 10316666Abstract: Methods for performing in situ balancing of an internal rotating component of a gas turbine engine are provided. The method can include inserting a repair tool through an access port of the gas turbine engine with the repair tool including a tip end positioned within the gas turbine engine and a material supply end positioned outside the gas turbine engine. The tip end of the repair tool is positioned adjacent to a surface of the internal rotating component of the gas turbine engine. A new material is supplied from the material supply end of the repair tool to the tip end of the repair tool; and is expelling from the tip end of the repair tool in a direction of the surface of the rotating component such that the new material is added onto a portion of the rotating part.Type: GrantFiled: April 12, 2016Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: David Scott Diwinsky, Herbert Chidsey Roberts
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Patent number: 10316667Abstract: Disclosed is an apparatus for decreasing a thrust of a radial flow turbine. The apparatus includes a rotary shaft having an axial through-hole in the interior thereof, a rotor assembled in the rotary shaft and having a rotor hub and rotor blades formed on an outer peripheral surface thereof, a casing configured to isolate the rotary shaft and the rotor from the outside, and a shaft seal configured to maintain a seal between the rotary shaft and the casing.Type: GrantFiled: June 29, 2016Date of Patent: June 11, 2019Assignee: Korea Maritime University Industry-Academic Cooperation FoundationInventors: You Taek Kim, Do Yeop Kim, Jun Seong Kim
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Patent number: 10316668Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall that forms a portion of an outer periphery of at least one cavity and at least one curved turbulator that extends from said wall.Type: GrantFiled: January 31, 2014Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mosheshe Camara-Khary Blake, Lisa K. Osborne, Thomas N. Slavens
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Patent number: 10316669Abstract: A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.Type: GrantFiled: October 26, 2017Date of Patent: June 11, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jean-Louis Romero, Jean-François Frerot
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Patent number: 10316670Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.Type: GrantFiled: December 4, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventors: Robert J. Morris, Barry K. Benedict
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Patent number: 10316671Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.Type: GrantFiled: July 17, 2015Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Pitchaiah Vijay Chakka, James D. Hill, David R. Pack
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Patent number: 10316672Abstract: A method for fabricating an airfoil includes forming a diffuser section in an exterior surface of the airfoil. The diffuser section is defined by at least an outer surface and an inner surface that converge at a stop surface. The method also includes positioning a drilling element of a drilling device on the stop surface. The method further includes orienting the drilling element at a first angle relative to the exterior surface. The method also includes forming, using the drilling element, a cooling channel extending through the airfoil from the stop surface to an interior surface, thereby forming the cooling channel at substantially the first angle.Type: GrantFiled: September 26, 2013Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: Aaron Ezekiel Smith, John Wesley Harris, Jr.
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Patent number: 10316673Abstract: Damping systems are provided for a rotor blade platform. The damping system may include a blade platform defining a damper pocket and a CMC wedge damper positioned within the damper pocket. The CMC wedge damper has at least one damper angled surface parallel to a longitudinal axis. The damper pocket comprises a pocket angled surface positioned about the at least one damper angled surface.Type: GrantFiled: March 24, 2016Date of Patent: June 11, 2019Assignee: General Electric CompanyInventor: Matthew Mark Weaver
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Patent number: 10316674Abstract: A carrier segment for forming a carrier section for one or more gas turbine engine components, the carrier segment including a carrier wall extending between front and rear carrier ends and having a circumferential profile, the carrier segment being configured for defining radially inwardly thereof a chamber for receiving cooling air from an outboard feed source via the front end, wherein the circumferential profile of the carrier wall is undulating, e.g. with a simple waveform configuration or a more complex arrangement of interleaved series of oppositely oriented part-conical surface formations.Type: GrantFiled: September 25, 2015Date of Patent: June 11, 2019Assignee: ROLLS-ROYCE plcInventor: Meirion Watkin
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Patent number: 10316675Abstract: A seal device of a turbine includes: at least one step surface disposed on a radially outer surface of a rotor blade facing a first radial-directional gap or on an outer peripheral surface of a rotor facing a second radial-directional gap, the at least one step surface facing upstream in a flow direction of a fluid and dividing the radially outer surface of the rotor blade or the outer peripheral surface of the rotor into at least two sections in an axial direction of the rotor; at least two seal fins protruding toward the at least two sections, respectively, from a surrounding member or the stationary vane, and facing the at least two sections via a seal gap, respectively, the at least two seal fins forming a cavity which extends over the at least one step surface in the axial direction of the rotor between each other.Type: GrantFiled: December 16, 2015Date of Patent: June 11, 2019Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Hideaki Sugishita
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Patent number: 10316676Abstract: A sealing device for sealing between coaxial shafts of a turbomachine, the sealing device including an elastic ring having a circular central opening allowing a sliding connection with an internal shaft, an external surface configured to engage with an internal surface of a portion of an external shaft, two retaining components situated one on either side of the elastic ring and allowing the elastic ring an axial clearance, wherein the elastic ring is a profile section.Type: GrantFiled: December 12, 2013Date of Patent: June 11, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventor: Jonathan Boris Baptista
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Patent number: 10316677Abstract: A cover band assembly of a blade row of stator or rotor blades is provided. The cover band assembly comprises a blade row that is arranged inside a main flow path of a continuous-flow machine and has multiple blades which respectively have a front edge and a rear edge; and a cover band of the blade row that is at least partially embedded in a component or a component group as regarded in a longitudinal section of the continuous-flow machine, wherein a cavity is formed that surrounds the cover band and is connected to the main flow path by way of two cavity openings, wherein the front cavity opening is provided upstream of the front edge and the rear cavity opening is provided downstream of the rear edge of the blades of the blade row. Here, the cover band has a leading edge and a trailing edge.Type: GrantFiled: April 8, 2016Date of Patent: June 11, 2019Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KIGInventor: Volker Guemmer
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Patent number: 10316679Abstract: A seal structure (2) for sealing a gap between a first structure body (10) and a second structure body (51). The seal structure includes: a peripheral surface formed on one of the first structure body and the second structure body; a plurality of seal fins (5) provided at intervals in the axial direction so as to form clearances (m) together with the peripheral surface and protrusions that form re-adhesion edges between pairs of axially adjacent seal fins; the re-adhesion edges being locations at which leak currents (SL) re-adhere that have passed through a clearance (mA) of an upstream seal fin; and the protrusions forming first cavities in which eddies (B1) are created that flow along the upstream seal fin toward the second structure body, and second cavities in which currents (B2) are created that cause a contraction current effect on a clearance (mB) of a downstream seal fin.Type: GrantFiled: January 29, 2015Date of Patent: June 11, 2019Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Toyoharu Nishikawa, Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Shin Nishimoto, Kazuyuki Matsumoto, Hidekazu Uehara
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Patent number: 10316680Abstract: A turbine is provided with a seal device. The seal device includes: at least one step surface disposed in a region of an outer peripheral surface of a rotor facing a shroud of a stationary vane in the radial direction of the rotor, the at least one step surface facing upstream in a flow direction of the fluid and dividing the region of the outer peripheral surface into at least two sections in an axial direction of the rotor: at least two seal fins protruding toward the at least two sections from the stationary vane and facing the at least two sections via a seal gap; and a swirling-component application portion disposed on an end side of the shroud of the stationary vane with respect to the axial direction of the rotor and configured to be capable of applying a swirling component to the fluid flowing toward the seal gap.Type: GrantFiled: December 16, 2015Date of Patent: June 11, 2019Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Hideaki Sugishita
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Patent number: 10316681Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.Type: GrantFiled: May 31, 2016Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: Jagata Laxmi Narasimharao, Thomas Ory Moniz, Mohamed Musthafa Thoppil, Bhaskar Nanda Mondal, Atanu Saha
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Patent number: 10316682Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.Type: GrantFiled: April 1, 2016Date of Patent: June 11, 2019Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce plcInventors: Daniel K. Vetters, Paul A. Davis, Simon L. Jones, Steven Hillier, Peter Broadhead
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Patent number: 10316683Abstract: A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.Type: GrantFiled: February 11, 2015Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventor: Paul W Palmer
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Patent number: 10316684Abstract: An active clearance control system for a gas turbine engine includes an air seal segment and a puller engageable with the air seal segment.Type: GrantFiled: February 6, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventor: Brian Duguay
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Patent number: 10316685Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.Type: GrantFiled: August 1, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventors: Timothy M. Davis, Brian Duguay
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Patent number: 10316686Abstract: An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring being configured to be coupled to a blade outer air seal (BOAS). The actuation system can also include an actuator coupled to at least one of the first end or the second end and configured to adjust a size of the gap such that a tip clearance between the BOAS and a blade tip is reduced in response to the size of the gap being reduced.Type: GrantFiled: November 22, 2016Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventors: Eric A. Hudson, Stephen K. Kramer
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Patent number: 10316687Abstract: A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.Type: GrantFiled: February 6, 2017Date of Patent: June 11, 2019Assignee: Rolls-Royce CorporationInventors: Richard C. Uskert, Joseph P. Lamusga, Aaron D. Sippel
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Patent number: 10316688Abstract: A turbomachine including an exhaust housing, including a plurality of arms, the space separating the arms defining openings in which there circulates a primary air flow of the turbomachine, at least one conduit, a) configured to collect a compressed air flow at one of the ends of same, b) the other end of the conduit being connected to at least one opening of the exhaust housing, so as to insert the collected air flow into the primary air flow, the collected air flow having, when inserted into the opening, a Mach number less than or equal to 0.5.Type: GrantFiled: January 20, 2015Date of Patent: June 11, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Abdelkader Benyahia, Jean-Michel Boiteux, Maxime Delabriere, Matthieu Fiack, Eddy Stephane Joel Fontanel, Alberto Martin Matos, Helene Orsi, Philippe Rembry, Olivier Renon, Giuliana Elisa Rossi
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Patent number: 10316689Abstract: A controller for a gas turbine engine is disclosed. The controller is configured to measure a first rotational speed of a shaft of the engine at a first end of the shaft and to measure a second rotational speed of the shaft at a second end. The first end may be coupled to a turbine of the engine and the second end may be coupled to a compressor of the engine. The controller is further configured to determine a shaft twist angle as a function of the first rotational speed and the second rotational speed, determine whether the shaft twist angle is within a predetermined shaft health monitoring range, and record the shaft twist angle. The controller may be configured to generate a maintenance alert in response to determining that the shaft twist angle is within the predetermined shaft health monitoring range.Type: GrantFiled: August 22, 2016Date of Patent: June 11, 2019Assignee: Rolls-Royce CorporationInventor: William S. Fletcher
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Patent number: 10316690Abstract: A method and machine for validating an investigated sensor within a sensor group includes receiving sensor data from sensors of the sensor group measuring the same physical property, calculating a deviation of the sensor data received from the investigated sensor within the sensor group from sensor data reconstructed based on the sensor data received from all other sensors of the sensor group, and signaling a sensor fault of the investigated sensor if the calculated deviation is outside of a trusted range.Type: GrantFiled: July 16, 2014Date of Patent: June 11, 2019Assignee: Siemens AktiengesellschaftInventors: Vladislav Chepel, Mikhail Kalinkin, Alexander Loginov
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Patent number: 10316691Abstract: An oil film damper of a bearing structure is located between facing surfaces of two bearings. The oil film damper includes two protrusions protruding inward in a radial direction from an inner circumferential surface of a main body portion, an oil guiding passage penetrating through from the protrusion to an outer circumferential surface of the main body portion and guiding a lubricating oil from the outer circumference of the main body portion to the bearing, an inclined surface provided on a side opposite to the adjacent surface adjacent to the bearing in the protrusion and having an inner diameter gradually increasing as the diameter is separate from the adjacent surface in the rotation axis direction of the shaft, and an oil discharge hole provided between the two protrusions of the main body portion and discharging the lubricating oil to an outside from an inside of the main body portion.Type: GrantFiled: November 22, 2016Date of Patent: June 11, 2019Assignee: IHI CorporationInventor: Tomokazu Murayama
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Patent number: 10316692Abstract: A method of suppressing shaft vibration of a turbocharger capable of being driven by a motor includes: a specific-vibration-state determination step of determining whether a rotor shaft of the turbocharger is in a specific vibration state in which a magnitude of shaft vibration of the rotor shaft is, or is likely to be, greater than a predetermined magnitude; an excited state determination step of determining whether the motor is in an excited state in which an exciting voltage is applied to the motor; and a vibration suppression execution step of applying the exciting voltage to the motor if it is determined that the rotor shaft is in the specific vibration state in the specific-vibration-state determination step and it is determined that the motor is not in the excited state in the excited state determination step.Type: GrantFiled: December 20, 2016Date of Patent: June 11, 2019Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Tadashi Yoshida, Musashi Sakamoto, Ryoji Sasaki, Yoshihisa Ono, Hidetaka Nishimura, Takeshi Tsuji
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Patent number: 10316693Abstract: An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.Type: GrantFiled: September 24, 2013Date of Patent: June 11, 2019Assignee: AIRBUS OPERATIONS GMBHInventors: Ralf-Henning Stolte, Udo Krause, Bruno Stefes, Christian Mueller, Florian Elken, Uwe Wollrab
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Patent number: 10316694Abstract: Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum, niobium, and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980° C.Type: GrantFiled: January 14, 2016Date of Patent: June 11, 2019Assignee: Garrett Transportation I Inc.Inventors: Pavan Chintalapati, Marc Wilson, Rayad Benchiheub, Philippe Renaud, Gary Agnew, Nicolas Devulder, Ted Pozniak
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Patent number: 10316695Abstract: The present disclosure is directed to a composite component defining a component aperture extending between a first surface and a second surface. The composite component includes an insert having an insert annular wall positioned in the component aperture. The insert annular wall defines an insert aperture therethrough. An insert flange extends radially outwardly from the insert annular wall and contacts the first surface of the composite component. The insert flange includes a diameter about 1.5 times to about 5 times greater than a smallest diameter of the component aperture defined by the composite component.Type: GrantFiled: December 10, 2015Date of Patent: June 11, 2019Assignee: General Electric CompanyInventor: Bernard James Renggli
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Patent number: 10316696Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.Type: GrantFiled: May 8, 2015Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: Mehdi Milani Baladi, Abdus Shamim, Joseph Anthony Cotroneo
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Patent number: 10316697Abstract: A steam turbine exhaust chamber cooling device includes a plurality of spray nozzles, and the plurality of spray nozzles inject spray water from an injection port to the turbine exhaust chamber. Here, a center line of the injection port is inclined with respect to a radial direction of a turbine rotor so that the plurality of spray nozzles inject the spray water in a direction counter to a rotation direction of the turbine rotor. An inclination angle ? at which the center line of the injection port is inclined to a forward side of the rotation direction with respect to the radial direction of the turbine rotor is in a relationship represented by the following formula (A), 25°???45°??(A).Type: GrantFiled: June 3, 2016Date of Patent: June 11, 2019Assignee: KABUSHIKI KAISHA TOSHIBAInventors: Xiaolan Wang, Yasuteru Kawai
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Patent number: 10316698Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.Type: GrantFiled: May 23, 2016Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David J. Candelori, Brandon Spangler
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Patent number: 10316699Abstract: A line arrangement for a motor vehicle, preferably for a waste heat utilization system of a motor vehicle. The line arrangement includes one or more lines for conducting a fluid medium and is distinguished, in particular, by the fact that at least one line comprises at least one textile hose or is configured as at least one textile hose, and the textile hose has a textile structure and an inner sheath.Type: GrantFiled: July 22, 2016Date of Patent: June 11, 2019Assignee: MAN Truck & Bus Österreich GesmbHInventors: Gottfried Raab, Josef Klammer, Stefan Robausch
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Patent number: 10316700Abstract: A combine cycle power plant is presented. The combine cycle power plant includes a gas turbine, a heat recovery steam generator, a main steam turbine and a supercritical steam turbine. The supercritical steam turbine may be operated as a separate steam turbine that may be not a single steam turboset with the main steam turbine. The supercritical steam turbine receives supercritical steam generated in the heat recovery steam generator to produce power output. Exiting steam from the supercritical steam turbine may be routed to the main steam turbine. The supercritical steam turbine may be operated at a rotational speed that is higher than a grid frequency. The rotational speed of the supercritical steam turbine may be reduced to the grid frequency via a gearbox.Type: GrantFiled: January 25, 2016Date of Patent: June 11, 2019Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Michael S. Briesch, Ankur Deshmukh, Thorsten Wolf
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Patent number: 10316701Abstract: An overhead valve actuation mechanism for an engine includes a camshaft that is rotatably supported by the cylinder head and includes one or a plurality of valve cams. The camshaft operates opening and closing of an intake valve and an exhaust valve via the valve cam. The only one camshaft is disposed within the one cylinder head. The camshaft has an axis center biased to a side of the exhaust valve with respect to a cylinder axis line as viewed from an axial direction of the camshaft.Type: GrantFiled: August 15, 2017Date of Patent: June 11, 2019Assignee: SUZUKI MOTOR CORPORATIONInventors: Koichi Tanaka, Kunio Arase
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Patent number: 10316702Abstract: An assembly for a valvetrain having a valve, a lash adjuster, and a lobe. The assembly includes a shaft, a bearing supported by the shaft for engaging the lobe, and a rocker having a pad for the valve and a socket for the lash adjuster. Walls are disposed between the pad and socket, have inner and outer wall surfaces, and define a valley for the shaft. Upwardly-opening arc-shaped bearing surfaces are disposed longitudinally between the pad and socket spaced laterally from each other and support the shaft when the bearing engages the lobe. A retention element formed in each wall with a depressed portion spaced from the outer wall surface and a lip portion arranged under the depressed portion extends into the valley above the bearing surfaces such that the shaft is prevented from moving out of the valley in absence of engagement between the bearing and the lobe.Type: GrantFiled: September 8, 2016Date of Patent: June 11, 2019Assignee: GT TechnologiesInventors: John Edmund Brune, Scott P. Smith
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Patent number: 10316703Abstract: A stator-cover unit (1) for a camshaft adjuster designed for use in an internal combustion engine, having a toothed ring (2) for receiving a torque, there being integrally connected to said toothed ring a stator (3) in the form of a housing, having a locking cover (4) which is separate from the stator (3), wherein the locking cover (4) is connected rotationally conjointly to the stator (3), wherein the stator (3) and the locking cover (4), at least during assembly, are held rotationally conjointly secured in said position by means of a projection (9) on one of the two components, which projection engages with a form fit into a recess (11) on the other of the two components. A camshaft adjuster having a rotor and having a correspondingly designed stator-cover unit (1), wherein a piston can be introduced, movably in an axial direction, into an opening of the locking cover (4).Type: GrantFiled: January 18, 2013Date of Patent: June 11, 2019Assignee: Schaeffler Technologies AG & Co. KGInventors: Olaf Boese, Holger Brenner
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Patent number: 10316704Abstract: A vane cell adjuster including a central locking device for locking the rotor in a central locking position, wherein the central locking device has at least two spring-loaded locking pins which can be locked in a stator-fixed locking slotted guide and which, during a rotation of the rotor from the direction of an “early” or “late” stop position, lock into the central locking position from different directions in the locking slotted guide, wherein a locking pin forms a valve unit with the respective accommodation chamber, wherein in a first switch position of the valve unit, at least one first pressure medium line is connected to allow free flow to a second pressure medium line, and in a second switch position of the valve unit, the first pressure medium line is connected to allow flow via a check valve to the second pressure medium line, wherein the check valve is provided in the rotor outside of the locking pin.Type: GrantFiled: January 12, 2015Date of Patent: June 11, 2019Assignee: Schaeffler Technologies AG & Co. KGInventor: Torsten Zschieschang
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Camshaft for the valve drive of an internal combustion engine with a variable valve opening duration
Patent number: 10316705Abstract: A camshaft for a valve drive of an internal combustion engine having a variable valve opening time may include an outer shaft and an inner shaft that extends through the outer shaft, with the inner shaft being held rotatably with respect to the outer shaft. The camshaft may further include a cam having a multiple-piece configuration, comprising a first part cam and a second part cam. Either the first part cam or the second part cam may be connected fixedly to the outer shaft so as to rotate with it, and the other part cam may be connected fixedly to the inner shaft so as to rotate with it. The camshaft may also include a bearing inner ring of a shaft bearing that is held on the outer shaft, with one of two second part cams comprising an axial attachment that forms at least one part of the bearing inner ring.Type: GrantFiled: June 17, 2015Date of Patent: June 11, 2019Assignee: THYSSENKRUPP PRESTA TECCENTER AGInventors: Uwe Dietel, Bernd Mann, Michael Kunz, Martin Lehmann -
Patent number: 10316706Abstract: A camshaft adjuster for an internal combustion engine, having a stator, a rotor mounted rotatably in the interior of the stator, and a locking cover connected to the stator. A hydraulically actuatable locking element is received in the rotor and engages into the locking cover in at least one blocking position, so as to block a rotation of the rotor relative to the stator, and is arranged in at least one unlocking position so that the rotor can be rotated relative to the stator.Type: GrantFiled: January 26, 2015Date of Patent: June 11, 2019Assignee: Schaeffler Technologies AG & Co. KGInventors: Jochen Thielen, Olaf Boese, Torsten Zschieschang
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Patent number: 10316707Abstract: An output element (1) of a camshaft adjuster (8) is described, in which the output element (1) has a contact surface (2) for rotatably fixed connection to a camshaft; the contact surface (2) has at least one outlet port (3) of an oil channel (4) of the output element (1), which may be situated opposite an outlet port of an oil channel of the camshaft in order to conduct hydraulic medium from the camshaft into the output element (1); the contact surface (2) has a structuring (6) in order to increase the torque transmission between the output element (1) and the camshaft; this structuring (6) is structure-free in the area (5) around the outlet port (3) and this area (5) is designed for sealing the outlet port (3) with respect to the surrounding environment.Type: GrantFiled: April 26, 2017Date of Patent: June 11, 2019Assignee: Schaeffler Technologies AG & Co. KGInventor: Juergen Weber
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Patent number: 10316708Abstract: A number of variations may include a product comprising a flexible member for an electric phaser actuator comprising: a plate, wherein the plate comprises a body; wherein the body has a thickness which is less than a width and a height of the body and wherein the body is constructed and arranged to attach to an output gear of an electric phaser actuator and wherein the body is constructed and arranged to mate with an input gear on a camshaft phaser.Type: GrantFiled: April 22, 2015Date of Patent: June 11, 2019Assignee: BorgWarner, Inc.Inventor: Mark M. Wigsten
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Patent number: 10316709Abstract: An internal combustion engine includes a cylinder head, a poppet valve having a seat within the cylinder head, a cam shaft on which is mounted an eccentrically shaped cam, and a rocker arm assembly comprising a rocker arm, a cam follower, and an electromagnetically actuated lash adjuster. The lash adjuster provides a continuously variable length fulcrum for the rocker arm. The actuator may be a piezoelectric stepper motor. The lash adjuster may be operative to vary a rate of internal exhaust gas recirculation and without requiring crank angle data.Type: GrantFiled: September 20, 2016Date of Patent: June 11, 2019Assignee: Eaton Intelligent Power LimitedInventors: Austin Robert Zurface, David Gerard Genise, Hongbin N. Wang, Sachin Wadikhaye
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Patent number: 10316710Abstract: An oil supply control device includes: an adjusting device which adjusts an oil discharge amount according to an input control value to adjust a hydraulic pressure; a hydraulic controller which outputs the control value to the adjusting device; a memory which stores a first initial control value corresponding to a first target hydraulic pressure at which a hydraulic actuating device is not activated, and a second initial control value corresponding to a second target hydraulic pressure at which the hydraulic actuating device is activated; and a determination portion which compares oil initial characteristics represented by the first and second initial control values with oil characteristics represented by first and second control values, to perform oil determination as to whether or not a viscosity of the oil has changed, the first control value being input before increase of the hydraulic pressure, the second control value being input after increase.Type: GrantFiled: February 7, 2017Date of Patent: June 11, 2019Assignee: MAZDA MOTOR CORPORATIONInventor: Masanori Hashimoto
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Patent number: 10316711Abstract: An internal combustion engine includes a cam shifting system having a shifting unit rotatably fixed and axially moveable with respect to a camshaft. The shifting unit includes at least two cams configured to be selectively brought in contact with a cam follower and provided with a base circle and with at least one cam lobe. The shifting unit is provided with at least one groove having a shifting portion. A driving pin is operable to be selectively engaged with and disengaged from the shifting portion of the groove. Engagement between the driving pin and the shifting portion of the groove moves the shifting unit with respect to the camshaft. During the movement of the shifting unit the cam follower engages at least a portion of at least one cam lobe.Type: GrantFiled: December 12, 2016Date of Patent: June 11, 2019Assignee: GM GLOBAL TECHNOLOGY OPERATIONS LLCInventor: Davide Di Nunno
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Patent number: 10316712Abstract: Described herein are lubricant compositions that include combinations of lubricant additives that are effective at improving the surface finish of a range of manufactured materials and equipment. In particular, friction modifiers and antiwear additives are employed to decrease surface roughness of additive manufactured (AM), e.g., 3D printed, materials and equipment in concert with maximizing energy efficiency.Type: GrantFiled: December 8, 2016Date of Patent: June 11, 2019Assignee: EXXONMOBIL RESEARCH AND ENGINEERING COMPANYInventors: Michael R. Douglass, David J. Baillargeon, Smruti A. Dance
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Patent number: 10316713Abstract: A recirculation valve for a pump having a regulator spool, a first resilient biasing member and a control valve. The first resilient biasing member biases the regulator spool in a first position in which flow of a liquid from a first port of the pump to a second port of the pump is prevented. The control valve controls the force required to move the regulator spool against the first resilient biasing member to a second position in which flow of the liquid from the first port to the second port is enabled.Type: GrantFiled: February 18, 2016Date of Patent: June 11, 2019Assignee: CONCENTRIC BIRMINGHAM LIMITEDInventors: Paul Shepherd, Mark Pieczko