Patents Assigned to Roll-Royce Deutschland Ltd & Co KG
  • Bleed air outlet in the bypass duct of a turbofan engine
    Patent number: 9097259
    Abstract: A bleed air outlet provided in the bypass duct of a turbofan engine includes a bleed air tube protruding into the bypass duct and a cover having a plurality of air outlet openings provided in the top of the cover, with the cover being conceived as an elongate, essentially oval, shell-like aerodynamic fairing element (3) which, while extending in the longitudinal direction of the bypass duct, is provided with a longitudinally convexly curved and transversely essentially straight top (10) and sidewalls (11) arcuately extending from the latter to an inner bypass duct wall. Such a design of the bleed air outlet reduces pressure losses, acoustic emissions and vibrations in the bypass duct.
    Type: Grant
    Filed: July 14, 2011
    Date of Patent: August 4, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Rotor device for a jet engine with a disk wheel and several rotor blades
    Patent number: 9080455
    Abstract: The present invention proposes a rotor device for a jet engine with a disk wheel and several rotor blades connected to said disk wheel, with the rotor blades being arranged in each case via a blade root substantially in the axial direction inside recesses of the disk wheel. Several locking segments are provided in the recesses of the disk wheel for axially locking the rotor blades, said locking segments interacting on the one hand with grooves of the rotor blades and on the other hand with at least one groove of the disk wheel. In the area of the groove of at least one of the rotor blades between the groove of the rotor blade and a locking segment there is a positive fit preventing a relative movement between the rotor blades and the locking segments.
    Type: Grant
    Filed: June 11, 2012
    Date of Patent: July 14, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Ulf Gerstberger
  • Cooled turbine blades for a gas-turbine engine
    Patent number: 9051841
    Abstract: The present invention relates to a cooled turbine blade for a gas-turbine engine having at least one cooling duct (14) extending radially, relative to a rotary axis of the gas-turbine engine, inside the airfoil and air-supply ducts (12) issuing into said cooling duct, characterized in that the cooling duct (14) extends into the blade root (6) in order to generate close to the wall a cooling airflow moved at high circumferential velocity and radially in helical form and that in the area of the blade root (6) at least one nozzle-shaped air-supply duct (12) issues into the cooling duct (14) tangentially or with a tangential velocity component.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: June 9, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Erik Janke, Jens Taege, Thomas Schiessl, Sebastian Meier, Heinz-Peter Schiffer, Nils Winter, Knut Lehmann
  • Oil supply system for an aircraft engine
    Patent number: 9046002
    Abstract: An oil supply system for an aircraft engine, includes at least one oil circuit including an oil tank having a closing valve associated with an outlet opening of the oil tank into a suction line, an oil pump, and at least one consumer to be supplied oil via a pressure line. A negative pressure relief line having a shut-off valve is connected to the suction line for ensuring pressure relief in the suction line after shutdown. Via a diaphragm volume flow limiter alternatively incorporated into the relief line, the suction line can also be connected permanently to the pressure line. A negative pressure occurring in the suction line after shutdown of the engine when the closing valve is closed and the plastic deformation of the suction line as well as a reduction of the pump suction capacity are thus avoided.
    Type: Grant
    Filed: March 2, 2012
    Date of Patent: June 2, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Christian Homeyer
  • Fuel injection nozzle with film-type fuel application
    Patent number: 9033263
    Abstract: A fuel injection nozzle for a gas turbine combustion chamber with a film applicator (1) is provided with several fuel openings (2). Center axes (5) of the fuel openings (2) through the film applicator (1), with regard to their radial orientation, are essentially parallel to the main flow direction (6) of the air.
    Type: Grant
    Filed: October 19, 2004
    Date of Patent: May 19, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Leif Rackwitz
  • Accessory gearbox device for a jet engine
    Patent number: 9032702
    Abstract: An accessory gearbox for an engine having at least one accessory gearbox shaft connectable to an auxiliary unit and driveable by a drive shaft, the drive shaft being operatively connectable to an engine shaft of the engine. At least one auxiliary unit can be arranged on the drive shaft and/or in the area of the operative connection between the drive shaft and the engine shaft and/or on an accessory gearbox shaft connectable to a further auxiliary unit.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: May 19, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Juergen Beier
  • Bloom mixer for a turbofan engine
    Patent number: 9027323
    Abstract: An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow duct includes an air-guiding element (13) arranged upstream of a thin-walled, corrugated part (6b) of the bloom mixer (6) for branching off a cold partial airflow and/or a hot partial airflow from the bypass duct and from the core flow duct of the engine. An air control device (14) is assigned to the air-guiding element (13) for leading the branched-off cold airflow or hot airflow along the inner surface and/or the outer surface of the bloom mixer (6) in order to deflect its corrugated part (6b) radially inwards or outwards on the basis of a temperature difference between an inner and an outer surface effected by the hot and/or cold partial airflow.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Robert Thies
  • Transport securing device of an aircraft gas turbine
    Patent number: 9027902
    Abstract: A transport securing device of an aircraft gas turbine includes a securing element, which at its two end areas is each provided with a first and a second connecting element, with the first connecting element being designed to be suitable for fastening to a front suspension device and the second connecting element being designed to be suitable for fastening to a rear suspension device of an aircraft gas turbine.
    Type: Grant
    Filed: July 8, 2013
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Marcel Schmidt, Alexander Krentz
  • Method for repairing rotor blades
    Patent number: 9027244
    Abstract: In a method for repairing worn or damaged rotor blades of an aircraft engine, laser cladding for the reconstruction of the blade tips is not performed in a continuous welding process along the blade edge but during a cycle-by-cycle rotation of the rotor blades attached to a rotor disk, in only one limited section of the respective blade edge for each cycle. The method reduces time expenditure for the repair of the blades and improves the tribological properties of the blade material in the area of the repaired blade tip.
    Type: Grant
    Filed: May 30, 2011
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Josef Nebesni
  • Apparatus and method for shot peening of blade mounting areas on a rotor arrangement disc
    Patent number: 9027375
    Abstract: An apparatus for shot peening blade mounting areas on a disc of a rotor includes a peening nozzle unit which streams shot peening media along a longitudinal axis. The unit includes a nozzle outlet which extends at least partially in a circumferential direction of the unit, and a deflection arrangement with a deflection area for the media. The deflection area is at least partially cone or half-hyperboloid shaped, such that the media passes the nozzle outlet over an angle range in circumferential direction after being deflected by the deflection arrangement. A method for shot peening the blade mounting areas positions the unit in a slot profile of a blade mounting area, and guides the unit along the contour of the slot profile with the nozzle outlet facing the contour of the slot profile to approximately uniformly peen the contour of the slot profile.
    Type: Grant
    Filed: September 8, 2014
    Date of Patent: May 12, 2015
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Straaltechniek International B.V.
    Inventors: Wolfgang Hennig, Marco Klijsen
  • Generator and accessory gearbox device with a generator
    Patent number: 9018806
    Abstract: The present invention proposes a generator for arrangement on a shaft of an accessory gearbox of an engine with a stator and with a rotor which can be coupled to a shaft of the accessory gearbox of the engine and which is rotatably mounted relative to the stator, where a stator area receiving the stator can be separated from a rotor area receiving the rotor. The rotor can be supplied with cooling medium in the rotor area. It furthermore proposes an accessory gearbox of an engine with a drive shaft operatively connectable to a main shaft of the engine and with at least one generator arranged on a shaft of the accessory gearbox.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Juergen Beier, Soeren Braun
  • Gas-turbine combustion chamber with a cooling-air supply device
    Patent number: 9016067
    Abstract: A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall 6 to be cooled. The cooling-air supply device includes at least one air-supply duct 8 which, in respect of its flow axis, is arranged vertically to the combustion chamber wall 6, with the air-supply duct 8 being flow-connected to at least one cooling duct 9. The air-supply duct 8 forms a throttle and has a smaller diameter than the cooling duct 9. The cooling duct 9 issues at a shallow angle, relative to its flow axis, to the surface of the combustion chamber wall 6 in a recess 10 of the combustion chamber wall 6, with the cooling duct 9 being designed to impart a swirl to the air flowing through it.
    Type: Grant
    Filed: October 18, 2011
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Miklos Gerendas
  • Sealing rings for a labyrinth seal
    Patent number: 9016692
    Abstract: In sealing rings for a labyrinth seal that are arranged on a rotationally symmetrical component and in frictional contact with a stationary run-in layer, a part of the sealing ring (8) that contacts the run-in layer is in the form of a wear protection ring segment (15) that is built up on a truncated sealing ring (14) and which includes a metal matrix (16) with wear protection particles (13) embedded therein. The manufacture of the wear protection ring segment is carried out by laser build-up welding, wherein the proportion of wear protection particles contained in the metal powder flow supplied to the laser beam can be controlled and increased in an edge or tip region of the sealing ring.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Haubold, Andreas Kohns
  • Gas-turbine balancing device
    Patent number: 9017029
    Abstract: The present invention relates to a gas-turbine balancing device with at least one annular groove provided on the outer circumference of at least one intermediate or high-pressure rotor of an intermediate or high-pressure compressor, with at least one balancing element being arranged in the annular groove, and with the balancing element being moveable in the circumferential direction along the annular groove and provided with a fixing device.
    Type: Grant
    Filed: May 4, 2012
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Sacha Pichel
  • ASSEMBLY FOR A FLUID FLOW MACHINE
    Publication number: 20150086344
    Abstract: A fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends and the main flow path boundary. At least one secondary flow duct having one opening each is provided in the main flow path boundary at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least one support component and at least one insertion component. The support component includes a recess extending in the circumferential direction that receives the at least one insertion component such that the support component surrounds the at least one insertion component largely on its sides not facing the main flow path, and where the insertion component completely surrounds or forms at least one secondary flow duct.
    Type: Application
    Filed: May 29, 2014
    Publication date: March 26, 2015
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker GUEMMER
  • Method and apparatus for etching the surfaces of integrally bladed rotors
    Patent number: 8980067
    Abstract: For electrolytically etching the surfaces of integrally bladed rotors (blisks) (6) made of nickel-base material for aircraft gas turbines, auxiliary cathodes (10), in addition to the main cathodes (3) provided in the electrolyte (1), are arranged in the area of the blades (9) remote from the electric contact points at the rotor disk (7). The auxiliary cathodes are adaptable in shape, arrangement and size to the blade and disk geometry, so that a uniform current flow from all parts of the rotor connected as anode via the electrolyte to the main and auxiliary cathodes is produced and an intense and uniform etching effect is achieved. This ensures a reliable structural assessment in all rotor areas and in particular also in the area of the integral blading.
    Type: Grant
    Filed: May 5, 2010
    Date of Patent: March 17, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Arno Secherling, Reinhard Koenig, Morgan Oparaugo
  • Accessory gearbox device for a jet engine
    Patent number: 8955403
    Abstract: The present invention proposes an accessory gearbox for an engine with a drive shaft operatively connectable to a main shaft of the engine, with an extension shaft being provided which can be put into a detachable operative connection to the drive shaft substantially coaxially to said drive shaft of the accessory gearbox At least one auxiliary unit can be detachably arranged on the extension shaft.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: February 17, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Juergen Beier, Gideon Venter
  • Method for the manufacture of a cutting tool
    Patent number: 8946585
    Abstract: A method for the manufacture of a cutting tool provided with a tool holder (1) to which a cutter (2) is separably attached, includes applying a generative production process to a tool base body (3) to create the tool holder (1) with a desired finished shape.
    Type: Grant
    Filed: June 11, 2007
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Gregor Kappmeyer
  • Lean premix burner of a gas-turbine engine provided with a flow-guiding element
    Patent number: 8943829
    Abstract: This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner center axis 1, is connected to a film applicator 3, which conically widens at the fuel exit side, as well as to an outer ring 4 concentrically arranged to the burner center axis 1 and surrounding at least the film applicator 3 at a certain distance, characterized in that an annular flow-guiding element 6 is provided in an annular duct 5 formed between the outer ring 4 and the film applicator 3 which, in the axial direction of the annular duct 5, is at least partly situated outside of the outer ring 4.
    Type: Grant
    Filed: May 2, 2011
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Imon-Kalyan Bagchi, Waldemar Lazik
  • Gas-turbine engine with bleed-air tapping device
    Patent number: 8944754
    Abstract: A gas-turbine engine with at least one compressor and at least one bleed-air tapping device, which includes an annular duct in a radially outer wall of a flow duct, and with an annular closing element, which is arranged in the region of the annular duct and can be moved in a substantially axial direction from a closed position to an open position, with the closing element having an annular flow divider projection which in the open position projects in the flow duct.
    Type: Grant
    Filed: May 10, 2012
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Sacha Pichel