Patents Assigned to Rolls-Royce Deutschland Ltd & Co.
  • Thrust reverser cascade element of an aircraft gas turbine
    Patent number: 10113507
    Abstract: The present invention relates to a thrust reverser cascade element of an aircraft gas turbine with a rigid frame and with several thrust reverser profiles mounted in the frame, wherein the thrust reverser cascade element is made of fiber-plastic composite.
    Type: Grant
    Filed: May 21, 2015
    Date of Patent: October 30, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Aleksa Starovic, Moritz Kuhtz, Werner Hufenbach
  • Group of blade rows
    Patent number: 10113430
    Abstract: The present invention relates to 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 meridional direction (m) and the circumferential direction (u), with the number N of the member blade rows being greater than/equal to 2 and (i) designating the running index with values between 1 and N. Here, a front member blade row with front blades (i) having a leading edge and a trailing edge as well as a rear member blade row with rear blades (i+1) having a leading edge and a trailing edge are provided.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: October 30, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Volker Guemmer
  • Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
    Patent number: 10100918
    Abstract: A device with a torque-proof first structural component and a second structural component that is connected at least in certain areas in a rotatable manner to the first structural component, wherein hydraulic fluid can be guided to lubrication points via the first structural component and the second structural component. The second structural component is embodied with blade areas which are extending substantially at a defined angle in the radial direction inside the second structural component and between which transmission areas for hydraulic fluid of the second structural component are provided, with their flow cross sections decreasing in the transmission areas in the flow direction of the hydraulic fluid.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: October 16, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Gideon Venter
  • Vibration damper
    Patent number: 10100643
    Abstract: A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom. Each blade has a suction side and a pressure side and includes a shank, a platform and a main portion, the main portion being radially outward of the shank and separated therefrom by the platform. At least one cavity is defined, each radially inward of the platforms and between a suction side of the shank of one blade and a pressure side of the shank of an adjacent blade. The rotor includes at least one damper, the damper including a main body in contact with at least one blade and a deflector nose. The deflector nose extends from the main body into the cavity.
    Type: Grant
    Filed: November 24, 2014
    Date of Patent: October 16, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Ioana Negulescu, Peter Davison
  • Transfer couplings
    Patent number: 10087779
    Abstract: A transfer coupling includes a static component and a rotatable component arranged concentrically, the static component including a first number of radially extending ports and the rotatable component having a second number of radially extending ports the radially extending ports arranged in a common circumferential plane wherein the ports are configured and arranged, in use, to homogenize a flow area for a fluid being transferred through the ports and thereby create a homogenous volume flow.
    Type: Grant
    Filed: April 5, 2016
    Date of Patent: October 2, 2018
    Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Stephan Uhkötter, Ulrich Adamczewski, Jack Francis Colebrooke
  • Gas turbine having at least two shafts designed as hollow shafts at least in some areas and arranged coaxially relative to one another
    Patent number: 10082037
    Abstract: The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages. An operating pressure is applied, in the area limited by the shafts in the axial direction of the shafts, to facing effective areas of the sealing elements, while the pressure prevailing in the area outside the shafts in the axial direction acts on effective areas of the sealing elements facing away from one another. A ratio between the outer diameters limiting the facing effective areas and the inner diameters likewise limiting these effective areas is in each case greater than or equal to 1.25.
    Type: Grant
    Filed: October 5, 2015
    Date of Patent: September 25, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Gideon Venter
  • Rotor of a turbine of a gas turbine with improved cooling air routing
    Patent number: 10082031
    Abstract: A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.
    Type: Grant
    Filed: March 3, 2016
    Date of Patent: September 25, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Markus Weinert, Tobias Leymann
  • Engine cowling
    Patent number: 10081435
    Abstract: An engine cowling, comprising a housing part, at least one door element, and a hinge, wherein the hinge fixates the door element at the housing part in an openable and closable manner, wherein the hinge includes a first hinge element, a second hinge element and a bolt, and wherein the hinge includes an adjustment device that can be adjusted in such a manner that a relative position of the door element to the housing part can be altered.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: September 25, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Ispir I. Ciprian
  • Gas-turbine engine with oil cooler in the engine cowling
    Patent number: 10082079
    Abstract: An engine cowling of an aircraft gas-turbine engine with a core engine and a bypass duct surrounding the latter, with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, and with stator vanes arranged in the bypass duct, where recesses for removing fluid from the bypass duct are provided in the area of the stator vanes on the inside of the front cowling, where the fluid discharged through the recesses is routed by means of flow ducts through the front cowling, brought into contact with at least one heat exchanger, and subsequently discharged to the environment.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: September 25, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Sascha Poenick
  • Method and device for machining the blade tips of a compressor rotor of a gas turbine
    Patent number: 10076816
    Abstract: A method and a device for processing blade tips of a mounted compressor rotor of a gas turbine. The compressor rotor includes a blade row with blades to be processed, and a blade row with blades that are not to be processed. The blade row not to be processed is accommodated in a stationary protective housing, which encloses the blade row. The blade row to be processed is processed by a processing machine during a rotation of the compressor rotor.
    Type: Grant
    Filed: September 17, 2015
    Date of Patent: September 18, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Andre Bretschneider
  • Device and method for bleeding compressor air in a turbofan engine
    Patent number: 10077719
    Abstract: A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement includes air guiding devices to guide compressor air into the secondary duct upstream of the fan stator relative to the flow direction in the secondary duct, past the stator vanes of the fan stator in a separate duct in the axial direction and is only mixed with the air of the secondary duct downstream of the fan stator. The separate duct is formed by a plurality of hollow structures extending in the longitudinal direction each between two adjacent stator vanes of the fan stator, with the hollow structures having a closed circumference in cross-section.
    Type: Grant
    Filed: February 13, 2014
    Date of Patent: September 18, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Mats Mojem, Andreas Scholz
  • Engine cowling of a gas turbine with thrust-reversing device and adjustable outlet nozzle
    Patent number: 10066582
    Abstract: An engine cowling of an aircraft gas turbine having a front cowling and a single rear cowling movable in the axial direction. By a drive device, the rear cowling is movable into different positions including a closed cruise position, a partially opened maximum thrust position and a completely opened thrust-reversing position. The drive device includes at least two actuators arranged in series relative to one another and actuated independently of one another, the actuators having power supply systems separated from one another and separately operating, where one of the actuators is designed for the maximum thrust position and the other actuator for the thrust-reversing position. The rear cowling can be locked in the maximum thrust position or the thrust-reversing position by two independent locking devices.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: September 4, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Gas turbine combustion chamber with a shingle attachment by means of catching elements
    Patent number: 10060626
    Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.
    Type: Grant
    Filed: December 13, 2016
    Date of Patent: August 28, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Kay Heinze, Stefan Penz, Ivo Szarvasy
  • Joint between components
    Patent number: 10054007
    Abstract: A joint assembly between a first gas turbine engine casing and a second gas turbine casing, the first gas turbine engine casing having a plurality of circumferentially spaced attachment points and the second gas turbine casing having a plurality of circumferentially spaced attachment points for securing the first gas turbine casing and the second gas turbine casing together, wherein each attachment point on the first gas turbine casing is circumferentially offset from a respective attachment point on the second gas turbine casing, and connected by a flexure member that permits limited relative movement of the attachment point on the first gas turbine engine casing and its respective attachment point on the second gas turbine casing.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: August 21, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Air guiding device and turbo engine with air guiding device
    Patent number: 10054054
    Abstract: An air guiding device for an aircraft engine, characterized in that it has at least one valve element which is moveable between a first position, in particular an open position, and a second position, in particular a closed position, wherein in the first position of the at least one valve element, through a combined effect with at least one first air guiding element that is arranged inside the air flow, a cooling air flow can be guided from an air flow into a hollow space between the housing and the core engine of the aircraft engine, and the at least one first air guiding element is aligned at least approximately in parallel to the air flow for the purpose of reducing flow resistance. The invention also relates to an aircraft engine comprising at least one air guiding device.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: August 21, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Matthijs Van Der Woude
  • FLUID TRANSFER COUPLING
    Publication number: 20180231115
    Abstract: A fluid transfer coupling comprises a first shaft assembly a second shaft assembly, and a seal assembly. The first shaft assembly comprises a first shaft and an annular fin attached to the first shaft, the annular fin having one or more internal passages extending therethrough. Each internal passage connects a centre portion of the first shaft to a radially outwardly facing side of the annular fin. The second shaft assembly comprises a second shaft and an annular trough extending radially outwardly of the second shaft.
    Type: Application
    Filed: February 15, 2018
    Publication date: August 16, 2018
    Applicants: ROLLS-ROYCE plc, Rolls-Royce Deutschland Ltd & Co KG
    Inventors: David P. SCOTHERN, Stephan UHKÖTTER
  • Stator of a turbine of a gas turbine with improved cooling air routing
    Patent number: 10041352
    Abstract: A stator of a turbine of a gas turbine, having a flow duct in which stator vanes are arranged, each vane having an outer and an inner vane platform, and each having a cooling air chamber formed by adjacent vane platforms for passing through cooling air, characterized in that the resultant cooling air chamber and/or a platform intermediate gap are designed such that starting from a side of the vane platform facing the adjacent vane platform, at least one outflow pocket open to a platform upper side and connected to the cooling air chamber is formed, and that in the wall of the cooling air chamber, at least one cooling air pocket opened radially inwards to the cooling air chamber and limited by an intermediate element or a sealing strip is formed and opens to the platform intermediate gap.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: August 7, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Markus Weinert, Tobias Leymann
  • Burner seal for gas-turbine combustion chamber head and heat shield
    Patent number: 10041415
    Abstract: The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the burner, with a burner seal being provided between the heat shield and the burner, characterized in that the heat shield is provided in the area of the recess with an annular groove, in which is arranged at least one elastic sealing element forming the burner seal.
    Type: Grant
    Filed: April 29, 2014
    Date of Patent: August 7, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Michael Ebel
  • Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
    Patent number: 10041579
    Abstract: A device includes a torque-proof first structural component and a second structural component rotatably connected to the first component. Hydraulic fluid is guided to lubrication points via the components. A sealing device seals an interface between the components. The interface includes a transition area limited by areas of the components that overlap in the radial direction and which carries hydraulic fluid, and which is connected to supply areas for hydraulic fluid of the first component and transmission areas for hydraulic fluid of the second component. The hydraulic fluid forms a floating hydrodynamic bearing between the components. The sealing device includes at least one thread area in the area of a surface of the second component or of the first component that is facing towards the surface of the first component or the second component.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: August 7, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Gideon Venter
  • Aero engine with a bearing chamber and an appliance for introducing oil
    Patent number: 10041410
    Abstract: An aero engine with a bearing chamber, which is confined by a first wall area and a second wall area which is embodied so as to be rotatable with respect to the first wall area and in which at least one bearing appliance as well as at least one appliance for introducing oil are arranged. Oil can be introduced into the bearing chamber via at least one appliance for introducing oil substantially against a rotational direction of the first wall area and/or of the second wall area and substantially tangentially to at least one surface of at least one wall area that is facing the bearing chamber.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: August 7, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Juergen Beier