Patents Assigned to Roll-Royce Deutschland Ltd & Co KG
  • Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
    Patent number: 8246478
    Abstract: On a low-pressure turbine shaft made of fiber-composite material, the connection to the metallic driven protrusion or the driving protrusion (1), respectively, is made via an adapter (3) formed onto the latter, with pylons (6) extending beyond the circumferential area of the latter and on which the fibers (4) are deflected and guided in accordance with the fiber orientation in the fiber-composite material, enabling high torsional forces to be transmitted via the small connecting zone.
    Type: Grant
    Filed: November 5, 2009
    Date of Patent: August 21, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Raimund Grothaus
  • Centrifugal oil separator for an aircraft engine
    Publication number: 20120204723
    Abstract: On a centrifugal oil separator for an aircraft engine for separating the oil particles contained in the vent air, a metallic foam body (7), into which the loaded vent airflow (3) is introduced, is firmly integrated into a hollow-type engine shaft (1), while high-voltage electrodes (6), which electrostatically charge the oil droplets in the vent air, are arranged outside the engine shaft (1) within the vent airflow (3) forwarded to the engine shaft (1). The simply designed oil separator, which can be space-savingly arranged and cost-effectively produced, ensures efficient separation of even minute oil droplets from the air-oil mixture.
    Type: Application
    Filed: April 29, 2011
    Publication date: August 16, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Robert ANGST
  • Method for the manufacture of a blisk
    Patent number: 8242406
    Abstract: A method for manufacturing integrally bladed rotors by laser brazing a rotor disk (1) made of a nickel or titanium-base material to blades (3) made of titanium aluminide. A brazing metal similar to the blade material is used, which is introduced into the laser beam (4) as brazing power jet (5) and whose heat capacity, which is controlled by the melting temperature and the volume of the molten metal bath This provides for melting of the disk material and alloying with this material, but not for melting of the blade material, to which it is connected by adhesion. Such blisk features a low blade weight, reduced centrifugal effects and enhanced service life.
    Type: Grant
    Filed: May 15, 2009
    Date of Patent: August 14, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Hermann Mohnkopf
  • Fluid flow machine including rotors with small rotor exit angles
    Patent number: 8235658
    Abstract: A fluid flow machine includes at least one rotor blade row designed for high work coefficients, which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor, in its trailing edge area, is essentially orientated in meridional direction, which essentially corresponds to the meridional flow direction.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: August 7, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Compressor stator with partial shroud
    Patent number: 8235654
    Abstract: A gas-turbine axial compressor has a casing 3 and a rotatable shaft 6, which form an annular duct, in which at least one stator 2 and one rotor 4 are arranged. A shroud 21 is arranged at a free end of the stator 2 vanes, which extends over part of the axial length of the stator 2. A rotor platform 23 of at least one rotor 4 extends axially beneath a further part of the axial length of the stator 2, at which no shroud 21 is arranged.
    Type: Grant
    Filed: March 18, 2009
    Date of Patent: August 7, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Bearing-chamber pressure system
    Patent number: 8235647
    Abstract: A gas turbine has a rear bearing chamber 2 including a bearing arrangement 1. A vent valve 14 vents the bearing chamber 2 as a function of relative pressure of the bearing chamber.
    Type: Grant
    Filed: December 8, 2008
    Date of Patent: August 7, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Arnaud Pisseloup, Brian Giessel
  • Gas-turbine compressor with bleed-air tapping
    Patent number: 8220276
    Abstract: A gas-turbine compressor has a casing (1) in which a rotor hub (2) is rotatably borne, and a compressor duct (9) being disposed between the casing (1) and the rotor hub (2), in which at least one rotor (4), which is rotatable about a machine axis (5), and one stator (5) are arranged. Recesses (12) of a bleed-air tapping device (6) are provided in the casing (1), which—in at least one circumferential area (11)—are arranged circumferentially to each other recess (12) and include a circumferential leading edge (16) in the circumferential direction and a circumferential trailing edge (17), each of which includes an identical angle ?E with the surface (18) of the casing (1).
    Type: Grant
    Filed: March 18, 2009
    Date of Patent: July 17, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Henner Schrapp
  • Stator vanes of a stator vane cascade of an aircraft gas turbine
    Patent number: 8221087
    Abstract: A method for manufacturing a stator vane 7 of a stator vane cascade 6 of a fan structure of an aircraft gas turbine, includes circumferentially welding two essentially flat metallic sheets 10, 11. A space between the sheets 10, 11 is formed in an injection mold by a filling pressure during a plastics injection process.
    Type: Grant
    Filed: April 29, 2009
    Date of Patent: July 17, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine
    Patent number: 8220586
    Abstract: A method for reducing noise emissions of an aircraft engine (3) having a gas turbine (7), includes providing a hot gas layer underneath at least one noise-emitting area of the aircraft engine.
    Type: Grant
    Filed: June 18, 2010
    Date of Patent: July 17, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Predrag Todorovic
  • Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
    Patent number: 8221080
    Abstract: At a propeller (1) or a fan (2) of an aircraft engine, part of the inflowing air—at the air stagnation point forming at the tip (8a) of the hub cone (8)—is conducted into an interior of a hub cone via air inlet openings (9) and, via air outlet openings (10) in an area with minimum static pressure at the downstream end of the hub cone, on a circumference of the latter and at a velocity essentially corresponding to the velocity of the air inflow, is injected into a thick boundary layer on the hub cone, essentially in the direction of flow, thereby accelerating the boundary layer to the velocity of the air inflow. This enables the inflow of air also to the root areas (4a, 6a) of the fan blades/propeller blades (4, 6), to be effected at an aerodynamically favorable, less steep inflow angle.
    Type: Grant
    Filed: July 23, 2009
    Date of Patent: July 17, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • GAS-TURBINE LEAN COMBUSTOR WITH FUEL NOZZLE WITH CONTROLLED FUEL INHOMOGENEITY
    Publication number: 20120174588
    Abstract: A gas-turbine lean combustor includes a combustion chamber (2) and a fuel nozzle (1) which includes a pilot fuel injection (17) and a main fuel injection (18). The main fuel injection (18) includes central recesses (23) for a controlled inhomogeneous fuel injection, the number of said recesses on the circumference ranging from 8 to 40 and said recesses having an angle of inclination ?2 in circumferential direction of 10°??2?60° and an axial angle of inclination ?1 relative to the combustor axis (4) between ?10°??1?90°.
    Type: Application
    Filed: March 8, 2012
    Publication date: July 12, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Leif RACKWITZ, Imon-Kalyan BAGCHI, Thomas DOERR
  • Blade shroud with aperture
    Patent number: 8202039
    Abstract: A fluid flow machine includes a main flow path in which at least one row of blades (3, 4) is arranged, and a blade shroud (2) which forms a confinement of the main flow path in the area of a blade row (3, 4) and is arranged in a recessed cavity (10) of a surrounding physical structure (11). The cavity (10) so formed between the shroud (2) and the surrounding physical structure (11) is provided with an annular connection (14) to the main flow path at least on the outflow side of the blade shroud (2), and with the blade shroud (2) being penetrated by at least one secondary flow path (16) which, commencing at a location of high pressure on the shroud (2), issues at a surface wetted by the main flow.
    Type: Grant
    Filed: June 23, 2009
    Date of Patent: June 19, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Blade shroud with protrusion
    Patent number: 8202044
    Abstract: A fluid-flow machine has a main flow path, in which at least one row of blades (1) is arranged, and a shroud (2) embedded in a cavity (3) of a component, with the component and the blades being in rotary movement relative to each other. The shroud (2), as referred to an axial direction of the fluid-flow machine is arranged between two reference points (A) and (B) at the periphery of the main flow path of the fluid-flow machine and projects beyond a rectilinear connection of the reference points (A) and (B) into the flow path in at least one location of the circumference and in at least one of the areas of the leading or trailing edge of the appertaining blade row.
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: June 19, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • FLUID-FLOW MACHINE - BLADE WITH HYBRID PROFILE CONFIGURATION
    Publication number: 20120148396
    Abstract: A blade for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles (7, 9, 10) arranged one behind the other in the flow direction are provided, of which each has substantially the shape of a blade profile, where a passage (8) is provided between each two partial profiles and is passed through by fluid from the blade pressure side to the blade suction side.
    Type: Application
    Filed: December 8, 2011
    Publication date: June 14, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Volker GUEMMER
  • Fluid return in the splitter of turbomachines with bypass-flow configuration
    Patent number: 8192148
    Abstract: A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages.
    Type: Grant
    Filed: August 30, 2007
    Date of Patent: June 5, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • REPAIR METHOD FOR A SANDWICH-LIKE COMPONENT
    Publication number: 20120125523
    Abstract: A gas-turbine casing includes a sandwiched structure of a wall 30, a honeycomb structure 31 and a top layer 29, with the wall 30, the honeycomb structure 31 and the top layer 29 being bonded by epoxy resin. A repair method for the casing includes a first working step where the top layer 29 and the honeycomb structure 31 are removed mechanically in an area to be repaired. Afterwards, the surface of the wall 30 is cleaned of the epoxy resin by a laser beam. In a further working step, at least one prefabricated replacement piece is bonded in place.
    Type: Application
    Filed: November 18, 2011
    Publication date: May 24, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Juergen DUPRE
  • GAS-TURBINE COMBUSTION CHAMBER WITH A COOLING-AIR SUPPLY DEVICE
    Publication number: 20120117973
    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: Application
    Filed: October 18, 2011
    Publication date: May 17, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos GERENDAS
  • Method of manufacturing integrally designed rotor wheels to exhibit an essentially identical natural frequency and mass using chemical etch machining
    Patent number: 8171632
    Abstract: In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life.
    Type: Grant
    Filed: December 8, 2008
    Date of Patent: May 8, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Arnold Kuehhorn, Thomas Klauke
  • DRIVE SHAFT, IN PARTICULAR RADIAL SHAFT FOR A GAS-TURBINE ENGINE
    Publication number: 20120094777
    Abstract: A drive shaft, in particular a radial shaft for a gas-turbine engine, includes a metallic and hollow shaft shank 1 with load transfer elements 2, 10, 11 integrally formed onto its ends. The shaft shank 1 includes a metal tube 3, 9 prefabricated as a semi-finished part, designed only for transmission of torsional loads and having a constant wall thickness. An outer or inner reinforcement 5, 8 intended only for ensuring the necessary bending stiffness is provided on the outer and/or inner circumferential surface of the metal tube 3, 9 and made from a fiber-composite layer 13, 13? with fibers oriented in the longitudinal direction of the drive shaft. The inner fiber-composite layer 13 acting as outer reinforcement 5 is sheathed with an outer fiber-composite layer 14 made from fibers oriented at an angle of 60° to 90° relative to the longitudinal direction.
    Type: Application
    Filed: October 10, 2011
    Publication date: April 19, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Gerald HECHLER-STABBERT, Alexander PABST
  • Method for impingement air cooling for gas turbines
    Patent number: 8152463
    Abstract: In impingement air cooling of gas turbine components, cooling air velocity packs of a certain amplitude and a given frequency are applied to impingement air openings, with intervallic annular swirl structures being formed which penetrate a cross-flow and hit a component to be cooled with high intensity, thus providing for efficient cooling. In order to obtain annular swirl structures with optimum cooling effect, the Strouhal number, which is determined by a ratio of amplitude, frequency of the velocity packs and size of impingement air cooling openings, ranges between 0.2 and 2.0, and preferably between 0.8 and 1.2.
    Type: Grant
    Filed: February 15, 2008
    Date of Patent: April 10, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Frank Haselbach, Erik Janke, Jens Taege, Timm Janetzke, Wolfgang Nitsche, Matthias Reyer