Patents Issued in January 18, 2018
  • Publication number: 20180016899
    Abstract: A manipulator for providing drilling expendables to a drill head of an underground drill rig includes a gripper that is arranged to selectively grip and release the drilling expendables and to move the gripper between a first position facing a supply magazine and a second position facing the drill head. The manipulator is also arranged to automatically take and return expendables to and from the magazine and drill head. A supply device provides the expendables to a drill head of an underground drill rig having the supply magazine, and to an underground drill rig, as well as an underground mining vehicle.
    Type: Application
    Filed: January 21, 2015
    Publication date: January 18, 2018
    Inventors: Thomas GALLER, Martin KUPPPER, Andreas BISCHOF
  • Publication number: 20180016900
    Abstract: A mine bolt includes an elongated body having a first end and a second end positioned opposite the first end, with the elongated body having a first threaded section, a second threaded section, and a non-threaded section positioned between the first threaded section and the second threaded section. The non-threaded section is configured to yield under loading when the mine bolt is installed with grout in a bore hole.
    Type: Application
    Filed: July 10, 2017
    Publication date: January 18, 2018
    Inventors: Lumin Ma, Dakota Faulkner, John C. Stankus
  • Publication number: 20180016901
    Abstract: Temperatures of exhaust gas upstream and downstream of an oxidation catalytic converter in an exhaust gas line of an internal combustion engine are measured and the differences analyzed to detect a leakage in the EGR evaporator.
    Type: Application
    Filed: July 18, 2017
    Publication date: January 18, 2018
    Applicants: AVL LIST GMBH, FPT INDUSTRIAL S.P.A., IVECO S.P.A.
    Inventors: MICHAEL GLENSVIG, Markus Thaler, Susanne Mahler
  • Publication number: 20180016902
    Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: Dennis Scott Holloway, Adebukola Oluwaseun Benson, Melbourne James Myers, Peter Paul Pirolla, William Scott Zemitis
  • Publication number: 20180016903
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier DELABRIERE, Vincent Nicolas Leonardon, Daniel Marius Man, Pascal Pierre Routier
  • Publication number: 20180016904
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Michel MERVANT, Laurent Patrick COUDERT, Jean-Armand Marc DESTOUCHES, Pascal Pierre ROUTIER
  • Publication number: 20180016905
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Pierre Hervé MARCHE, Maxime Didier DELABRIERE, Pascal Pierre ROUTIER, Guillaume Jochen SCHOLL
  • Publication number: 20180016906
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier DELABRIERE, Laurent Patrick COUDERT, Jean-Armand Marc DESTOUCHES, Daniel Marius MAN
  • Publication number: 20180016907
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Erwan Daniel BOTREL, Maxime Didier DELABRIERE, Daniel Marius MAN, Pierre Hervé MARCHE
  • Publication number: 20180016908
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Pierre ROUTIER, Maxime Didier DELABRIERE, Vincent Nicolas LEONARDON, Daniel Marius MAN
  • Publication number: 20180016909
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Marius MAN, Maxime Didier DELABRIERE, Pierre Hervé MARCHE, Pascal Pierre ROUTIER
  • Publication number: 20180016910
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Marius MAN, Maxime Didier DELABRIERE, Pierre Hervé MARCHE, Pascal Pierre ROUTIER
  • Publication number: 20180016911
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier DELABRIERE, Vincent Nicolas LEONARDON, Daniel Marius MAN, Pierre Hervé MARCHE
  • Publication number: 20180016912
    Abstract: A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
    Type: Application
    Filed: September 15, 2017
    Publication date: January 18, 2018
    Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
  • Publication number: 20180016913
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Pierre ROUTIER, Vincent Nicolas LEONARDON, Daniel Marius MAN, Pierre Hervé MARCHE
  • Publication number: 20180016914
    Abstract: A method of manufacturing a gas turbine engine component and said resulting component configuration are disclosed. The method includes providing a ceramic structure including a sacrificial ceramic core. The ceramic structure is inserted into a casting mold. A component material is introduced into the casting mold. The ceramic structure is removed after the component material has solidified to define a casted component having a cooling cavity of a heat exchanger segment formed in the wall structure of the component. The ceramic body of the sacrificial ceramic core defines a plurality of apertures and includes a trailing first pin and a leading first pin. The trailing first pin and the leading first pin are extended away from an inner surface of the body, and the leading first pin is spaced from the trailing first pin and in closer proximity to a leading edge of the body than the trailing first pin.
    Type: Application
    Filed: April 13, 2017
    Publication date: January 18, 2018
    Inventor: Mark O'Leary
  • Publication number: 20180016915
    Abstract: A turbomachine component having an aerofoil, such as a blade or a vane for a gas turbine engine, includes a suction side wall and a pressure side wall bordering an aerofoil cavity, and meeting at a leading edge and a trailing edge. The turbomachine component also includes a circumferentially extending first platform wherefrom the aerofoil extends radially. The first platform includes a first-platform cavity corresponding to a shape of the aerofoil and continuous with the aerofoil cavity. The first-platform cavity has a leading-edge end and a trailing-edge end corresponding to the leading edge and the trailing edge, respectively, of the aerofoil. The first-platform cavity at the trailing-edge end forms a protuberance within the first platform. The turbomachine component may optionally include a second-platform cavity in a circumferentially extending second platform. The second-platform cavity at its trailing-edge end forms an additional protuberance within the second platform.
    Type: Application
    Filed: July 12, 2017
    Publication date: January 18, 2018
    Applicant: Siemens Aktiengesellschaft
    Inventors: Mark Osborne, Martin Williams
  • Publication number: 20180016916
    Abstract: Various embodiments include a heat transfer device, while other embodiments include a turbine component. In some cases, the device can include: a body portion having an inner surface and an outer surface, the inner surface defining an inner region; at least one aperture in the body portion, the at least one aperture positioned to direct fluid from the inner region through the body portion; and at least one fluid receiving feature formed in the outer surface of the body portion, the at least one fluid receiving feature positioned to receive post-impingement fluid from the at least one aperture, wherein the at least one aperture does not define any portion of the at least one fluid receiving feature, and the at least one fluid receiving feature segregates relatively higher velocity post-impingement fluid from relatively lower velocity fluid within an impingement cross-flow region.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: Robert Frank Hoskin, James Albert Tallman
  • Publication number: 20180016917
    Abstract: Various aspects include a turbomachine component, along with a turbomachine and related storage medium. In some cases, the turbomachine component includes: a body defining an inner cavity, the body having an outer surface and an inner surface opposing the outer surface, the inner surface facing the inner cavity; and a mount coupled with the inner surface of the body, the mount including: an impingement baffle coupled with and separated from the inner surface of the body, the impingement baffle including a set of apertures configured to permit flow of a heat transfer fluid therethrough to contact the inner surface of the body; and a reclamation channel connected with the impingement baffle for reclaiming the heat transfer fluid.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: James Albert Tallman, Gary Michael Itzel
  • Publication number: 20180016918
    Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud.
    Type: Application
    Filed: July 10, 2017
    Publication date: January 18, 2018
    Applicant: MTU Aero Engines AG
    Inventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
  • Publication number: 20180016919
    Abstract: A structure includes a substrate, and a thermal barrier coating comprising a base material and one or more reflective layers disposed in the base material, each reflective layer having a plurality of reflective particulates. The structure can be a turbine blade, for example.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: Alexander Staroselsky, Thomas J. Martin
  • Publication number: 20180016920
    Abstract: A rotor assembly for a turbomachine includes a hub, a plurality of first blades, and a plurality of second blades. The hub includes an axis of rotation, a first face and an opposite second face, with each of the first face and the second face being normal to the axis of rotation. Each of the first blades includes a first blade root portion, and each of the second blades includes a second blade root portion.
    Type: Application
    Filed: June 16, 2017
    Publication date: January 18, 2018
    Applicant: ROLLS-ROYCE PLC
    Inventor: Jae-Hoon CHUNG
  • Publication number: 20180016921
    Abstract: A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventor: Anthony L. Schiavo
  • Publication number: 20180016922
    Abstract: A gas turbine engine has a crown locking device and a seal portion. The crown locking device and seal portion connect a transition duct to an inlet extension piece. The crown locking device and seal portion is located between a metallic integrated exit piece and a transition duct that is made of ceramic matrix composites.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventor: Anthony L. Schiavo
  • Publication number: 20180016923
    Abstract: A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.
    Type: Application
    Filed: July 14, 2017
    Publication date: January 18, 2018
    Applicant: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Jost IMFELD, Hans-Christian MATHEWS, Urs BENZ
  • Publication number: 20180016924
    Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one embodiment, a shroud segment for a gas turbine engine having a rotor blade stage and a nozzle stage is provided. The shroud segment comprises a forward end defining an outer wall of the rotor blade stage and an aft end defining an outer wall of the nozzle stage. The aft end defines at least a portion of an opening therethrough for receipt of a nozzle, and the forward end and the aft end form a single, continuous component. In another embodiment, a gas turbine engine is provided, having a shroud with a forward end positioned near a leading edge of a plurality of rotor blades of a rotor blade stage and an aft end positioned near a trailing edge of a plurality of nozzles of a nozzle stage. Methods of assembling a gas turbine engine also are provided.
    Type: Application
    Filed: July 18, 2016
    Publication date: January 18, 2018
    Inventors: Kirk Douglas Gallier, Charles William Craig, III
  • Publication number: 20180016925
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: December 29, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Marius MAN, Laurent Patrick COUDERT, Jean-Armand Marc DESTOUCHES, Thomas Michel MERVANT
  • Publication number: 20180016926
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: February 22, 2017
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Michel MERVANT, Renaud Gabriel ROYAN, Pierre Hervé MARCHE, Vincent Nicolas LEONARDON
  • Publication number: 20180016927
    Abstract: The present disclosure is directed to a sealing system for a turbine engine including an engine component, the engine component defining an oblique sealing surface defining an annular shape. The oblique sealing surface defines an oblique angle with a centerline of the engine component. The sealing system includes a seal housing and a seal ring. The seal housing is annular and includes a groove that is defined by a first sidewall, a second sidewall, and an end wall connecting the first sidewall and the second sidewall. The seal ring is positioned at least partially within the groove in the seal housing. The seal ring defines a seal contact surface for forming a seal with the oblique sealing surface of the engine component.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: Donald Michael Corsmeier, Donald Scott Yeager
  • Publication number: 20180016928
    Abstract: 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: Application
    Filed: December 16, 2015
    Publication date: January 18, 2018
    Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Hideaki Sugishita
  • Publication number: 20180016929
    Abstract: A nut for a turbine engine, in particular for axially locking a bearing race. The nut comprises a thread for screwing onto a part of the turbine engine, and a lock for ensuring the nut cannot rotate relative to the engine part. The nut further comprises at least one dynamic seal.
    Type: Application
    Filed: February 9, 2016
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Arnaud Michel Marie Accary, Alexandre Michel Henri Hasquenoph, Frédéric David Stéphane Rogues, Régis Eugène Henri Servant
  • Publication number: 20180016930
    Abstract: An adjustment ring of a variable turbine geometry of an exhaust gas turbocharger is disclosed. The adjustment ring may include at least a first ring segment and a second ring segment.
    Type: Application
    Filed: July 12, 2017
    Publication date: January 18, 2018
    Inventors: Joerg Jennes, Robert Jost, Dirk Lummer, Jochen Mueller
  • Publication number: 20180016931
    Abstract: An assembly, in particular for controlling variable pitch vanes in a turbine engine, comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes, in addition to a driving means for rotating the actuating ring around the casing. The assembly includes a slidingly connected passive element, one end of which is connected by a sliding pivoting link on the actuating ring and a second end is connected by a ball-joint link to the casing.
    Type: Application
    Filed: July 10, 2017
    Publication date: January 18, 2018
    Applicant: Safran Aircraft Engines
    Inventors: Kamel Benderradji, Blaise Bergan, Alain Marc Lucien Bromann, Suzanne Madeleine Coustillas, Lilian Yann Dumas
  • Publication number: 20180016932
    Abstract: An actuating device may include a housing having a first housing part made of plastic and a second housing part, and an electric motor arranged in the second housing part having a drive shaft projecting axially into the first housing part for driving an actuator arranged on an outside of the housing for coupling to the component to be actuated. The actuating device may also include a cooling channel formed in the second housing part and fluidically connected to coolant inlet and outlet connections provided on the outside of the housing, an electronic system arranged in the first housing part, an axial recess formed at least in a region of the electronic system on the first housing part, and an axial heat-conducting elevation provided on the second housing part and extending at least in the region of the electronic system axially into the recess.
    Type: Application
    Filed: July 11, 2017
    Publication date: January 18, 2018
    Inventors: Eugen Makarow, Edgar Salfeld, Florian Wetzel
  • Publication number: 20180016933
    Abstract: A method of mitigating soak-back in a gas turbine engine including an engine core compartment and an active engine core compartment cooling system are provided. The active engine core compartment cooling system includes an aperture extending through a core engine cowl forming a radially outer wall of the engine core compartment. The active engine core compartment cooling system also includes a cooling fan mounted within the engine core compartment and including a cooling fan inlet and a cooling fan outlet. The cooling fan inlet is coupled in flow communication with the aperture. The cooling fan outlet is coupled in flow communication with the engine core compartment. The active engine core compartment cooling system further includes a cooling fan controller configured to at least one of control a rotational speed of the cooling fan and control a position of at least one flow control valve coupled in series flow communication with the cooling fan.
    Type: Application
    Filed: July 12, 2016
    Publication date: January 18, 2018
    Inventors: Mohamed Elbibary, Daniel Jean-Louis Laborie
  • Publication number: 20180016934
    Abstract: According to one aspect, a method of releasing a fan blade for testing a turbofan engine includes providing an internal passage with a constant arc through an airfoil arranged about a blisk such that the constant arc of the internal passage aligns with a contour of the blisk. The method further includes packing the internal passage with a charge, modifying the airfoil such that the airfoil is released from the blisk evenly along a chordwise length of the airfoil, and detonating the charge such that the airfoil is released from the blisk at a selected time.
    Type: Application
    Filed: July 15, 2016
    Publication date: January 18, 2018
    Inventors: Christopher Hall, Graham Burkholder, Xuekun Sun, Jeff Crutchfield, Ben Hodgson, Dennes Kyle Burney
  • Publication number: 20180016935
    Abstract: A method of determining a faulty sensor of a sensor array of a gas turbine engine (10), the sensor array comprising at least first, second and third sensors (A, B, C), the method comprising the steps of: a. measuring a first set of sensor outputs (S1A, S1B, S1C) prior to engine startup from each sensor (A, B, C), and calculating a first difference (S1A-S1B, S1A-S1C, S1B-S1C) in the measured value for each sensor pair (A; B, A;C, B;C); b. after a period of time, measuring a second set of sensor outputs (S2A, S2B, S2C) prior to engine startup from each sensor (A, B, C), and calculating a second difference (S2A-S2B, S2A-S2C, S2B-S2C) in measured value for each sensor pair (A;B, A;C, B;C); c. calculating a further difference ((S1A-S1B) -(S2A-S2B), (S1A-S1C)-(S2A-S2C), (S1B-S1C)-(S2B-S2C)) between the calculated first and second differences for each sensor pair (A; B, A;C, B;C); and d.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 18, 2018
    Applicant: ROLLS-ROYCE PLC
    Inventor: David P SCOTHERN
  • Publication number: 20180016936
    Abstract: In the case of a device and a method for monitoring the service life of an engine or of a turbine having a compressor blisk and/or a turbine blisk, momentary stresses of blisk substructures, such as the blade (1), the disk (2), and the join region (3) between the blade (1) and the disk (2), are calculated on the basis of operating parameters that are measured in the course of engine or turbine operation; and accumulated damage to the individual substructures, that was caused by the momentary stresses, is estimated.
    Type: Application
    Filed: September 27, 2017
    Publication date: January 18, 2018
    Inventors: Eberhard Knodel, Hans-Peter Borufka, Hernan Victor Arrieta
  • Publication number: 20180016937
    Abstract: A gas turbine includes a main shaft connecting a turbine to a compressor and an additional shaft extending coaxially to the main shaft. The additional shaft has a first shaft section connected to the compressor and a second shaft section connected to the turbine, the shaft sections separated from each other by a gap. At mutually facing ends, the two shaft sections have mutually corresponding structures. The gap between the two shaft sections is dimensioned such that, upon a break of the main shaft, the mutually corresponding structures of the mutually facing ends of the two shaft sections come into interaction and rotate relative to one another as a result of their differing rotational speeds. The mutually corresponding structures are formed such that the two shaft sections are moved away from one other in the event of twisting of the two shaft sections.
    Type: Application
    Filed: July 11, 2017
    Publication date: January 18, 2018
    Inventors: Martin PANZNER, Enrique SIELAFF
  • Publication number: 20180016938
    Abstract: A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.
    Type: Application
    Filed: June 16, 2017
    Publication date: January 18, 2018
    Applicant: ROLLS-ROYCE plc
    Inventors: Phillip J. DOORBAR, Jason J. MADGE
  • Publication number: 20180016939
    Abstract: A gas turbine engine comprising a gearbox, the gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier, each planet gear being rotatably mounted in the carrier by at least one bearing, the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear, the sun gear, the planet gears and the annulus gear comprising gear teeth, the annulus gear having a length in the axial direction and an axially forward end and an axially rearward end and wherein the annulus gear is resiliently mounted to a supporting structure at both its axially forward and axially rearward ends.
    Type: Application
    Filed: July 6, 2017
    Publication date: January 18, 2018
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Christoph KLAUS
  • Publication number: 20180016940
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Application
    Filed: February 22, 2017
    Publication date: January 18, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier DELABRIERE, Pascal Pierre ROUTIER, Pierre Hervé MARCHE, Vincent Nicolas LEONARDON
  • Publication number: 20180016941
    Abstract: The annulus is bound by an inner hub wall and an outer casing and includes a support structure, the support structure bearing the inner hub wall; at least one spigot passing through the hub wall and at least one strut arranged to pass through the spigot of the inner hub wall and across the annulus. The strut has a first end having an abutment arm extending to form an abutment shoulder. Alignable holes pass through the abutment arm and the spigot and these holes are configured to receive a cross pin which is in turn configured to fit snugly through the holes. The configuration is such that, the abutment rim and abutment shoulder are located radially inwardly of the holes and cross pin and outside of the annulus.
    Type: Application
    Filed: July 10, 2017
    Publication date: January 18, 2018
    Applicant: ROLLS-ROYCE plc
    Inventor: Stephen MCDONAGH
  • Publication number: 20180016942
    Abstract: A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud.
    Type: Application
    Filed: March 5, 2015
    Publication date: January 18, 2018
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Keigo SAKAMOTO, Eigo KATOU, Youji AKIYAMA, Makoto OZAKI, Daigo WATANABE
  • Publication number: 20180016943
    Abstract: A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.
    Type: Application
    Filed: July 18, 2016
    Publication date: January 18, 2018
    Inventors: GUY LEFEBVRE, NICOLAS GRIVAS, VINCENT PARADIS
  • Publication number: 20180016944
    Abstract: An assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle remover, a second particle remover fluidly coupled which receives a particle-laden stream from the first particle remover, and a venturi having a fluidly coupled to the second particle remover to increase the pressure differential across the assembly.
    Type: Application
    Filed: July 14, 2016
    Publication date: January 18, 2018
    Inventors: Jared Peter Buhler, Christopher Charles Glynn, Corey Bourassa, Monty Lee Shelton, Robert Francis Manning, Victor Hugo Silva Correia
  • Publication number: 20180016945
    Abstract: An in-situ incremental reheating system configured to increase steam temperature and thermodynamic efficiencies of a steam turbine is disclosed. The system includes a pump; a radiant heater; piping inter-connecting the pump, radiant heater and steam turbine to create a flow circuit; and a heat transfer material configured to flow through the flow circuit and transfer heat directly to steam used in the steam turbine. The pump moves the heat transfer material through the flow circuit and the radiant heater regenerates the heat transfer material after the heat transfer material transfers heat to the steam.
    Type: Application
    Filed: February 26, 2016
    Publication date: January 18, 2018
    Inventors: Scott Alexander Hume, David Thimsen
  • Publication number: 20180016946
    Abstract: Optimizing power generation from waste heat in large industrial facilities such as petroleum refineries by utilizing a subset of all available hot source streams selected based, in part, on considerations for example, capital cost, ease of operation, economics of scale power generation, a number of ORC machines to be operated, operating conditions of each ORC machine, combinations of them, or other considerations are described. Recognizing that several subsets of hot sources can be identified from among the available hot sources in a large petroleum refinery, subsets of hot sources that are optimized to provide waste heat to one or more ORC machines for power generation are also described.
    Type: Application
    Filed: September 28, 2017
    Publication date: January 18, 2018
    Applicant: Saudi Arabian Oil Company
    Inventors: Mahmoud Bahy Mahmoud Noureldin, Hani Mohammed Al Saed, Ahmad Saleh Bunaiyan
  • Publication number: 20180016947
    Abstract: A method for preheating untreated water in a power plant having a water/steam circuit, the power plant has a steam producer, a steam turbine, and steam lines, of which at least some connect the steam producer to the steam turbine, wherein untreated water for producing deionized water is heated by means of wastewater from the water/steam circuit and the wastewater is added to the untreated water in order to heat the untreated water. A power plant is adapted for preheating untreated water by the method.
    Type: Application
    Filed: December 9, 2015
    Publication date: January 18, 2018
    Applicant: Siemens Aktiengesellschaft
    Inventor: Michael Haegel
  • Publication number: 20180016948
    Abstract: An energy storage apparatus includes a first circuit containing a first phase change material, second circuit containing a second phase change material, and a heat pump having a cold side heat exchanger thermally coupled to the first circuit and a hot side heat exchanger thermally coupled to the second circuit. The apparatus is operable in a charging mode, a storage mode, and a discharge mode. In the charging mode the heat pump is energized to cool the first phase change material and heat the second phase change material. In the storage mode the first phase change material is stored in a first storage vessel and the second phase change material is stored as a pressurized vapor in a second storage vessel. In the discharge mode vaporized first phase change material is expanded by a first expander, or the vaporized second phase change material is expanded by a second expander.
    Type: Application
    Filed: February 11, 2016
    Publication date: January 18, 2018
    Inventor: Adrian Charles Hutchings