Patents Assigned to Rolls-Royce Deutschland Ltd & Co KG
  • Patent number: 10619565
    Abstract: An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange interface surface has a conus angle that is divergent from the highlight axis.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: April 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Predrag Todorovic, Thomas Kubisch
  • Patent number: 10605254
    Abstract: A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: March 31, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Bjorn Ulrichsohn, Susanne Schruefer, Karl Schreiber
  • Patent number: 10591162
    Abstract: The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.
    Type: Grant
    Filed: November 12, 2014
    Date of Patent: March 17, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten Clemen
  • Patent number: 10584604
    Abstract: A blade row group arrangeable in a main flow path of a fluid-flow machine and including N adjacent member blade rows firmly arranged relative to one another in both the axial direction and the circumferential direction is provided. Here, a front member blade row with front blades as well as a rear member blade row with rear blades are provided in the meridional plane established by the axial direction and the radial direction. The blade row group has two main flow path boundaries. It is provided that the blades of the member blade rows are fixed to the one main flow path boundary in the surrounding structure by means of a blade root structure, and that the blades of the member blade rows on the other main flow path boundary are each firmly connected to a base.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: March 10, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Volker Guemmer
  • Patent number: 10584591
    Abstract: A rotor of a turbomachine includes a plurality of rotor blades, which each have a blade leading edge and a tip, the rotor blades forming a first group and at least one further group of rotor blades of different construction. It is provided that the rotor blades of the first group are nominal rotor blades, the rotor blades of the at least one further group each have a material cutout in the transition from the blade leading edge to the tip, the material cutout not being present in the case of the rotor blades of the first group, and the rotor blades of the first group and of the at least one further group form a non-periodic sequence in a circumferential direction.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: March 10, 2020
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Rolls-Royce plc
    Inventors: Maciek Opoka, Thomas Giersch, Bernhard Mueck, John Dodds, Chris Hall
  • Patent number: 10578029
    Abstract: An adjustment device for adjusting several guide vanes of the engine, wherein the adjustment device includes at least one adjusting element that couples with the guide vanes and is mounted in an adjustable manner, a connection element that couples with the adjusting element, as well as a crank shaft for controlling an adjusting movement of the adjusting element, and the crank shaft has at least one coupling element which couples with the connection element and at which the connection element is hinged to transform a rotational movement of the crank shaft about a longitudinal axis of the crank shaft into an adjusting movement of the adjusting element for adjusting the guide vanes. The crank shaft has a modular design with at least two shaft modules that are arranged behind each other along the longitudinal axis of the crank shaft.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: March 3, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Mats Rudolf Mojem
  • Patent number: 10570791
    Abstract: The present invention describes a device of a jet engine with at least one component arranged in a casing and designed rotatable relative to said casing. At least one air-oil volume flow can be passed out of an area of the jet engine into the casing. In accordance with the invention the air-oil volume flow can be introduced into the casing via an introducing facility at least approximately tangentially to an area of the rotatable component close to at least an outer circumferential area.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: February 25, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Juergen Beier
  • Patent number: 10570914
    Abstract: A compressor for a turbomachine, with at least one rotor disc and a space that is at least partially enclosed by the at least one rotor disc and that is arranged axially in front of or behind the at least one rotor disc, wherein vortex reducers are arranged inside the space, wherein the vortex reducers are connected to the structural components in a form-fitted and/or in a frictionally engaged manner partially via first scallops at a first structural component and partially via second scallops at a second structural component that is adjacent to the first structural component in the axial direction, wherein the first scallops and/or second scallops are arranged at a retaining ring, which can be connected or is connected to the first rotor disc and/or the second rotor disc. What is further described is a method for mounting a compressor.
    Type: Grant
    Filed: August 23, 2016
    Date of Patent: February 25, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Jens Lueddecke, Steffen Drevs
  • Patent number: 10557374
    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 been 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: Grant
    Filed: July 11, 2017
    Date of Patent: February 11, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Martin Panzner, Enrique Sielaff
  • Patent number: 10550722
    Abstract: A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box and the casing and/or the heat transfer device comprise at least one heat transfer and/or fluid flow guiding structure, in particular a ribbed surface, a finned surface and/or a studded surface, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: February 4, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thierry Sibilli, Bjorn Ulrichsohn, Jonas Schwengler
  • Patent number: 10550273
    Abstract: A method for determining temperature in a flow channel of a gas turbine positioned on a testing bench includes: arranging at least one rod-shaped element provided with a thermal paint coating inside the flow channel; operating the gas turbine on the testing bench in a defined operating mode, wherein the thermal paint coating of the at least one rod-shaped element changes its color depending on the temperature that the thermal paint coating is exposed to; detecting the color distribution of the thermal paint coating of the at least one rod-shaped element; and determining the temperature that has been present in the flow channel along the at least one rod-shaped element in the defined operating mode based on the detected color distribution. Another embodiment relates to a measuring device having a rod-shaped element provided with a thermal paint coating.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: February 4, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Knut Lehmann
  • Patent number: 10547258
    Abstract: An electric machine coupled to rotating machinery includes a rotor and a stator, and the method of control of an electric machine and an electric machine control system. The method includes sensing one or more parameters indicative of one or more resonance conditions of the rotating machinery, and comparing the sensed parameter to a predetermined threshold to determine whether the rotating machinery is operating at the resonance condition. Where the rotating machinery is determined to be operating at the resonance condition, adjusting a magnetic field of one or both of the rotor and the stator to provide a predetermined torque to the rotating machine, to modulate the stiffness of the rotational machinery, and thereby move the resonance condition away from the current rotating machinery conditions.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: January 28, 2020
    Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Lucia Ciciriello, Kevin Smith
  • Patent number: 10544942
    Abstract: A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to the outer combustion chamber wall and the inner combustion chamber wall by means of rivets that are arranged in a circumferentially distributed manner, and that subsequently the combustion chamber head is brought in position and is screwed together by means of threaded bolts and nuts to the arrangement of head plate, outer combustion chamber wall and inner combustion chamber wall, which is pre-mounted by means of the rivet.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 28, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Kay Heinze, Volker Herzog
  • Patent number: 10539447
    Abstract: A structural unit for arrangement at a hydraulic fluid tank of a jet engine that is embodied with an outlet appliance for draining hydraulic fluid. When the structural unit is arranged at a hydraulic fluid tank, the outlet appliance has an outlet opening that is facing towards the hydraulic fluid tank. The structural unit is further embodied with at least one measuring appliance, by means of which a filling level of a hydraulic fluid that is present inside the hydraulic fluid tank can be determined when the structural unit is arranged at a hydraulic fluid tank. A fixture appliance is provided for fixedly attaching the structural unit at a hydraulic fluid tank.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: January 21, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Gideon Venter, Andre Kalms
  • Patent number: 10533451
    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: Grant
    Filed: July 6, 2017
    Date of Patent: January 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Christoph Klaus
  • Patent number: 10526904
    Abstract: A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.
    Type: Grant
    Filed: April 18, 2017
    Date of Patent: January 7, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Markus Weinert, Tobias Leymann
  • Publication number: 20190388961
    Abstract: An investment casting pattern including: a consumable body formed of: a first body portion; and a second body portion; and a fastener arranged to form an interface between the first body portion and the second body portion, and to locate the first body portion relative to the second body portion, wherein the fastener is formed of a different material than the first body portion and the second body portion.
    Type: Application
    Filed: June 11, 2019
    Publication date: December 26, 2019
    Applicants: ROLLS-ROYCE plc, Rolls-Royce Deutschland Ltd & Co KG
    Inventors: David Stefan ISLES, Mareike WIEBALCK, Peter JESSON, Mark MULLAN, Christopher A HALL
  • Patent number: 10508714
    Abstract: A geared turbofan engine with a sun shaft driving a sun gear of planetary gearbox. The sun shaft having a front section proximal to the gearbox and a rear section distal from the gearbox. The outer diameter of the front section of the sun shaft is smaller than the outer diameter of the rear section of the sun shaft. The front section of the sun shaft having between two and four undulant sections, wherein each undulant section having at least one axial part extending in axial direction of the sun shaft and two diaphragm parts on either side of the at least one axial part extending in radial direction outward, the at least one axial part of the undulant section having an inner diameter smaller than the outer diameter of the front section of the sun shaft.
    Type: Grant
    Filed: October 5, 2017
    Date of Patent: December 17, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Tomasz Grubba
  • Patent number: 10500683
    Abstract: Methods for manufacturing a tandem guide vane segment that includes an outer platform, a front guide vane, and a rear guide vane, wherein the front guide vane and the rear guide vane are arranged in a firmly fixated manner with respect to one another. One method includes manufacturing an integral front segment section that includes the front guide vane and a front section of the outer platform, manufacturing an integral rear segment section that includes the rear guide vane and a rear section of the outer platform, and connecting the two segment sections to each other.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: December 10, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Oliver Koehne, Felix Goeppinger
  • Patent number: 10502144
    Abstract: A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: December 10, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dominic Boniface