Patents Assigned to Roll-Royce Deutschland Ltd & Co KG
  • Aircraft gas turbine thrust-reversing device
    Patent number: 9376986
    Abstract: An aircraft gas turbine thrust-reversing device has an engine cowling, the rear area of which is displaceable in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular space to a front and stationary area of the engine cowling. The rear area of the engine cowling is coupled to deflecting elements and blocker doors, which in the forward thrust position are arranged completely inside the front area of the engine cowling. A drive element is provided between the front area and the rear area, which effects the axial displacement of the rear area. The drive element is a two-stage drive element, effecting in a first stage an axial displacement by an axial partial displacement path, and in a second stage an axial displacement by the full axial displacement path.
    Type: Grant
    Filed: February 4, 2013
    Date of Patent: June 28, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
    Patent number: 9371778
    Abstract: The present invention relates to an engine casing of an aircraft gas turbine having a radially inner honeycomb-structured layer arranged on the engine casing in the flow direction upstream of a fan in the area of an inflow-side air inlet, characterized in that sound-absorbing elements are arranged radially outside at least one axial section of the honeycomb-structured layer, said elements extending in the axial direction and being arranged annularly next to one another in the circumferential direction.
    Type: Grant
    Filed: January 16, 2013
    Date of Patent: June 21, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Thomas Kubisch
  • Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
    Patent number: 9370739
    Abstract: The present invention describes a jet engine with at least one oil separator, through which an air-oil volume flow can be guided out of at least one area supplied with oil for separating the oil. In accordance with the invention the air-oil volume flow from the area supplied with oil can be introduced into the oil separator via an interior of an accessory gearbox casing. The air can be discharged from the oil separator via an air outlet and the oil via an oil outlet.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: June 21, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Juergen Beier, Gideon Venter
  • Method for producing a component by direct laser depositioning using first and second lasers operated at different powers
    Patent number: 9370789
    Abstract: A method for producing a component provided with a supporting structure includes using at least one first laser for layer by layer manufacturing of the component out of a powdery material, using at least one second laser for producing a supporting structure, supporting the component, layer by layer out of the powdery material and operating the at least one first laser with a lower power than a power of the at least one second laser.
    Type: Grant
    Filed: June 13, 2014
    Date of Patent: June 21, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Combustion chamber of a gas turbine
    Patent number: 9366436
    Abstract: A combustion chamber of a gas turbine with an outer combustion chamber wall and with tiles attached to the inner side of said wall or to a combustion chamber of the single-wall design, wherein the combustion chamber has in a center area, relative to the flow direction, a slot extending around the circumference of the combustion chamber and dividing the outer combustion chamber wall and the tiles for the supply of mixing air.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: June 14, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Thomas Doerr, Sebastian Bake
  • Assembly of an axial turbomachine and method for manufacturing an assembly of this type
    Patent number: 9366148
    Abstract: An assembly of an axial turbomachine includes at least one outlet guide vane of a compressor and a diffuser arranged downstream of the outlet guide vane in the flow direction. The outlet guide vane is connected to the compressor and the diffuser is connected to the combustion chamber, without there being a direct mechanical connection between the diffuser and the outlet guide vane.
    Type: Grant
    Filed: August 29, 2013
    Date of Patent: June 14, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • AIR INTAKE ARRANGEMENT
    Publication number: 20160160757
    Abstract: An intake for channeling air flowing past a propeller to an inlet of an aircraft engine driving the propeller through a drive shaft comprising: a static cowling extending about an axis and which flares from an upstream end, an intake slot formed in the flared portion which bounds a passage to the inlet of the aircraft engine, the intake slot opening over an arc that extends less than 360 degrees of the circumference of the cowling and having an axially rearward edge that blends into the cowling through a curve having a vertex, wherein the vertex is radially inside a projected extension of the flared portion from an upstream portion of the flared cowling across the intake slot.
    Type: Application
    Filed: November 30, 2015
    Publication date: June 9, 2016
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag TODOROVIC
  • Method for radiographically inspecting a component by means of X-ray beams using a smoothing agent and smoothing agent for carrying out the method
    Patent number: 9360438
    Abstract: The present invention relates to a method for radiographically inspecting a component by means of X-rays, where at least one component surface to be radiographed is provided with a surface structure, with at least the surface provided with the surface structure being smoothed by means of a smoothing material to level out the surface structure, with at least one organic compound and at least one metal powder being used as smoothing material, with the X-ray absorption behavior of the smoothing material essentially equaling the X-ray absorption behavior of the material of the component, as well as to a smoothing material for carrying out the method in accordance with Claim.
    Type: Grant
    Filed: August 9, 2011
    Date of Patent: June 7, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Josef Geitner
  • Tile fastening arrangement of a gas-turbine combustion chamber
    Patent number: 9341372
    Abstract: The present invention relates to a tile fastening arrangement of a gas-turbine combustion chamber having a combustion chamber wall with tiles fastened to said combustion chamber wall at a distance from the latter, characterized in that the tile is provided with an annular flange arranged on its side assigned to the combustion chamber wall, said flange being dimensioned to match a recess of the combustion chamber wall and fastened to the combustion chamber wall by means of a fastening element which engages in the combustion chamber wall.
    Type: Grant
    Filed: November 13, 2013
    Date of Patent: May 17, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Stefan Penz
  • Combustion chamber of a gas turbine
    Patent number: 9335048
    Abstract: The present invention relates to a combustion chamber of a gas turbine having an outer combustion chamber wall and an inner combustion chamber wall, where the inner combustion chamber wall, at its front end area relative to the direction of flow through the combustion chamber, is fixed to the outer combustion chamber wall and, at its rear end area, is held longitudinally movable at the outer combustion chamber wall.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: May 10, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Imon Kalyan Bagchi
  • Segmented combustion chamber head
    Patent number: 9328926
    Abstract: A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: May 3, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Stefan Penz, Miklos Gerendas, Sermed Sadig
  • Method for determining a flow behavior of a medium
    Patent number: 9330231
    Abstract: A method for determining a flow behavior of a medium uses at least one analysis device placed inside the medium. The at least one analysis device is freely moveable in the medium and supplies data characterizing at least one property of the medium flow behavior to a data evaluation device. The at least one property of the medium flow behavior is determined by the data evaluation device on the basis of the data in selected areas or in all areas through which the at least one analysis device flows with the medium.
    Type: Grant
    Filed: November 15, 2012
    Date of Patent: May 3, 2016
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Rolls-Royce PLC
    Inventors: Goetz G. Feldmann, Kelvin Hau-Kong Chan
  • Bearing device and turbomachine having a bearing device
    Patent number: 9328627
    Abstract: A bearing device, for example in a turbomachine is provided. Between bearing races of the anti-friction bearings and a casing component positioned adjacent the bearing races is arranged a device for converting an axial force between the anti-friction bearings into a torque at the bearing races in the manner of a ball screw or planetary screw assembly. The bearing races are connected to one another by a feedback mechanism such that a torque at one bearing race can be converted into an opposite torque at the other bearing race.
    Type: Grant
    Filed: November 19, 2012
    Date of Patent: May 3, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Sebastian Hennig
  • Aviation gas turbine thrust reversing device
    Patent number: 9328694
    Abstract: The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine.
    Type: Grant
    Filed: January 19, 2012
    Date of Patent: May 3, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Rolling tool device
    Patent number: 9327329
    Abstract: The present invention describes a rolling tool device for compression rolling of, in particular, blade elements of a rotor area of a jet engine provided with a tool carrier. The tool carrier is connectable to a carrier spindle. Furthermore, two pliers-type bodies are rotatably connected to the tool carrier. The pliers-type bodies are each provided with a rolling area, with a distance between the rolling areas being variable in dependence of the rotary movement of the pliers-type bodies. In accordance with the present invention, an axis of the carrier spindle in the state connected to the tool carrier passes between the rolling areas through a contact point present at a distance between the rolling areas equal to zero.
    Type: Grant
    Filed: April 12, 2012
    Date of Patent: May 3, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Goetz G. Feldmann, Karsten Roettger, Stefan Zenk
  • Gas-turbine combustion chamber with mixing air orifices and chutes in modular design
    Patent number: 9328665
    Abstract: The present invention relates to a gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber.
    Type: Grant
    Filed: July 22, 2013
    Date of Patent: May 3, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Doerr, Leif Rackwitz, Stefan Penz
  • Gas-turbine combustion chamber having non-symmetrical fuel nozzles
    Patent number: 9303875
    Abstract: The present invention relates to an annular gas-turbine combustion chamber having a radially outer and a radially inner combustion chamber wall relative to a machine axis, a combustion chamber head and a combustion chamber outlet nozzle, where the combustion chamber head includes several fuel nozzles spread over its circumference for supplying air and fuel, the latter exiting in an outlet surface of the fuel nozzles, where the respective fuel nozzle has a burner axis which is vertical to the outlet surface and where the intersections of the burner axes with the outlet surfaces define a circular burner centerline around the engine axis, characterized in that a cross-sectional area of the fuel nozzle radially outside the burner centerline is identical to a cross-sectional area radially inside the burner centerline.
    Type: Grant
    Filed: January 31, 2013
    Date of Patent: April 5, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Sound absorber, sound absorber assembly and an engine with a sound absorber assembly
    Patent number: 9303588
    Abstract: A sound absorber comprising a base body and a tongue (24). The base body has a bottom plate, a wall enclosing the bottom plate and an opening enabling the entry of air into the base body. The tongue has a fixed end, a free end and a central portion disposed between the fixed and the free end. The free end of the tongue is spaced from the wall and the bottom plate, and the central portion of the tongue is disposed to extend at least partially straight along a width direction. Furthermore, a sound absorber assembly can include at least two sound absorbers, and an engine, in particular, for an aircraft, comprising such a sound absorber and/or such a sound absorber assembly.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: April 5, 2016
    Assignees: Airbus Defence and Space GmbH, Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Reinhard Pongratz, Christoph Richter, Max Kern, Daniel Redmann
  • Nozzle with guiding devices
    Patent number: 9279387
    Abstract: A nozzle has a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements. A wall element connects a first guiding device and a second guiding device. At least some of the first azimuthal guide walls of the first guiding device and at least some of the second azimuthal guide walls of the second guiding device have differing axial lengths, so that first and second trailing edges thereof have differing axial positions.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: March 8, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Marco Rose, Rene Spieweg
  • Method for the manufacture of a workpiece with defined surface
    Patent number: 9278385
    Abstract: A method for manufacturing a workpiece 1, 2 uses a forming tool 4, 5 having a cavity 3. An embossing element 6 profiled on at least one surface is arranged on at least one surface of the forming tool 4, 5 for producing a surface structure, and with the profile of the embossing tool 6 is imparted to the surface of the workpiece 1, 2 during a forming process.
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: March 8, 2016
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, FormTech GmbH
    Inventors: Karl Schreiber, Werner Beck