Patents Assigned to Rolls-Royce Deutschland Ltd & Co KG
  • Emergency shutdown detection device for a gas turbine
    Patent number: 7782221
    Abstract: An emergency shutdown detection device for a gas turbine includes a longish, mechanically severable sensor element (5), in which at least one electric line (1 to 4) is provided, with at least one resistor (R1 to R3) being electrically connected to the electric line such that upon severance of the sensor element (5), the electrically connected resistor is electrically disconnected from the electrical line to alter a resistance value for the electrical line.
    Type: Grant
    Filed: April 5, 2007
    Date of Patent: August 24, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Gustavo Arguello, Clemens Chaskel
  • Ice strike sheathing ring for the fan casing of an aircraft gas turbine
    Patent number: 7780401
    Abstract: An ice strike sheathing ring (4) including several fiber compound layers for the fan casing of an aircraft gas turbine features breaking points (7) at a certain regular distance, so that, in case of destruction of the ice strike sheathing ring due to extreme ice strike, fragments of small size will be produced which together with the engine airflow will pass the exit guide vanes downstream of the fan without blocking the engine airflow or reducing engine thrust. With fiber compound layers enclosing a cavity or a core, the breaking points designed as slots (9) and/or assembly holes (8) are located in the inner wall (20) of the ice strike sheathing ring facing the engine airflow, while the outer wall (21) of the ice strike sheathing ring adjoining the fan casing is firmly attached to the latter via an adhesive film and a threaded safety connection.
    Type: Grant
    Filed: August 3, 2007
    Date of Patent: August 24, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Olaf Lenk, Uwe Dickert
  • Workpiece holding system for a machine tool
    Patent number: 7770499
    Abstract: A workpiece holding system for correctly locating disk-shaped workpieces in a work area of a machine tool, in particular for machining rotor disks of a gas turbine engine, includes a base plate (6) firmly attached to the machine tool (1) with vertically and radially adjustable clamping elements (7) for restraining the workpiece on an outer circumference in a correct position, as well as a plurality of differently dimensioned centering elements (12) and supporting elements (17), each adapted to a particular shape and size of the workpiece (2) to be machined and to the respective processing step, these centering (12) and supporting elements (17) being exchangeable and attachable to the base plate/machine tool by quick fasteners.
    Type: Grant
    Filed: April 2, 2007
    Date of Patent: August 10, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Matthias Biertz, Wolfgang Pieczeit, Patrik Scalla
  • METHOD FOR THE PROVISION OF A COOLING-AIR OPENING IN A WALL OF A GAS-TURBINE COMBUSTION CHAMBER AS WELL AS A COMBUSTION-CHAMBER WALL PRODUCED IN ACCORDANCE WITH THIS METHOD
    Publication number: 20100192588
    Abstract: A cooling-air opening in produced in a wall (6) of a gas-turbine combustion chamber using a laser beam. In a first operation, a recess (10c) with a first, larger cross-section is produced from the hot gas side in a partial area of the wall (6) at a shallow angle to the surface. In at least one subsequent operation, a recess (10b, 10a) with a second, smaller cross-section is produced through the entire material of the wall (6) at a shallow angle to the surface while deepening a partial area of the previous recess (10c). A step (12), which is produced between the two recesses in the two operations, is larger than a median coating thickness of a subsequently applied ceramic thermal barrier coating (14).
    Type: Application
    Filed: February 1, 2010
    Publication date: August 5, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos GERENDAS
  • ARRANGEMENT FOR THE REPAIR OF THE BLADES OF BLISK DRUMS BY MEANS OF LASER DEPOSITION WELDING
    Publication number: 20100176097
    Abstract: An arrangement for the repair of BLISK blades damaged at their leading and trailing edges by use of laser deposition welding, includes a laser source and laser optics for generating a focused laser beam (26) and a powder line (35) connected to a powder reservoir for supplying metal powder to be melted by the laser beam to the weld area. A modular, tubularly elongated welding apparatus (7) with a connection module (13) which is connected to a laser source and in which the entering laser beam is deflected in longitudinal direction and parallelized, and to the one side of the connection module (13) is connected to a camera module for a CCD camera (12) enabling the precise positioning of the welding apparatus and the deposition of the molten metal powder on the respective blade to be monitored and controlled.
    Type: Application
    Filed: January 12, 2010
    Publication date: July 15, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Leping ZHU
  • METHOD FOR THE MANUFACTURE OF THE BLADE TIPS OF ROTOR WHEELS MADE IN BLISK DESIGN
    Publication number: 20100175256
    Abstract: With a method for finish-machining the blade tips of rotor wheels made in BLISK design, the rotor wheel or multi-stage compressor rotor (1), is machined—blade by blade and stage by stage—at the blade tips (2) by a conical cutter (5) whose cutting edge (6) is oriented tangentially to the outside surface of the rotor wheel/compressor rotor and routed on the blade tip essentially along the centerline thereof, with the cutting force being introduced vertically to the tool axis and in the stiffest direction of the blade (3), i.e. the centerline (11) of the blade cross-section and the vertical axis extending from the centerline. The cutting action and the force introduction of the conical cutter at the blade tip allow production of blade tips with a geometrically precisely defined edge without setting the respective blades into vibration.
    Type: Application
    Filed: January 12, 2010
    Publication date: July 15, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Leping ZHU, Gregor RIEDEL
  • Leading edge configuration for compressor blades of gas turbine engines
    Patent number: 7744346
    Abstract: In a supersonic area, on a leading edge (2) of a compressor blade (1) for a gas turbine engine, a replaceable, longitudinally elastically deformable leading edge rail (7) with slender tip (11) and limited weight is positively held in a locating groove (3) and at a stop (6) and elastically locked by the curved blade form. While the maintenance effort is reduced, safe operation and long service life of the compressor (fan) are ensured.
    Type: Grant
    Filed: December 18, 2006
    Date of Patent: June 29, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Roland Heinrich
  • Generator-starter system for a multi-shaft engine
    Patent number: 7745950
    Abstract: In order to provide a high electric power for an aircraft via a generator driven by the engine, an additional free turbine is included in the hot-gas flow of the engine, which—equipped with generator-starter magnets (9) and surrounded by annularly arranged generator-starter coils (12)—forms a generator-starter turbine (5) and is connected to the high-pressure shaft (1) via an overrunning clutch (15), and hence, is also used for starting the engine.
    Type: Grant
    Filed: September 4, 2007
    Date of Patent: June 29, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Rudolf Lueck
  • MACHINE CONTROL FOR A NUMERICALLY CONTROLLED MACHINE TOOL
    Publication number: 20100161107
    Abstract: On a numerically controlled machine tool a sub-program is integrated into the given program for controlling the machine tool by which a periodic change of at least one cutting tool parameter is effected in one processing cycle, or also in several processing cycles, or in certain length and diameter zones of the workpiece characterized by tool vibrations and leading to inferior workpiece quality. By way of the periodic cutting parameter change, self-excited tool vibrations are avoided in these sensitive machining areas, thereby enabling tool wear to be reduced and workpiece quality improved. Furthermore, this intervention into the machining program is documentable and identically reproducible for each workpiece—independently of the expertise and personal judgement of the operator.
    Type: Application
    Filed: December 10, 2009
    Publication date: June 24, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Gregor KAPPMEYER, Wolfgang PIECZEIT
  • AIRCRAFT WITH TAIL PROPELLER-ENGINE LAYOUT
    Publication number: 20100155526
    Abstract: An aircraft propeller-engine layout includes at least one engine (10) arranged in a tail (2) of a fuselage (1) of an aircraft and has at least one propeller arrangement, with a shaft of the propeller (6, 7) being connected to a shaft (21) of the engine (10) via at least one transfer shaft (12).
    Type: Application
    Filed: September 25, 2009
    Publication date: June 24, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dimitrie NEGULESCU
  • SENSOR BRACKET FOR AT LEAST ONE SENSOR ON A GAS TURBINE
    Publication number: 20100148027
    Abstract: A sensor bracket (1) for at least one sensor (5) on a gas turbine, made of at least one fiber-composite material (10), with the fibers (7) embedded in the fiber-composite material (10) being oriented at an angle ? relative to an axis x extending vertically to a free end edge (3) of the sensor bracket (1) in a plane established by the fibers (7), and the stiffness and the natural frequencies of the sensor bracket (1) being defined by said angle ?, with the natural frequencies of the sensor bracket (1) lying outside of the frequency range of the sensor bracket (1), which includes the measuring range of the sensor (5).
    Type: Application
    Filed: December 11, 2009
    Publication date: June 17, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Olaf LENK
  • SEGMENTED SEALING LIPS FOR LABYRINTH SEALING RINGS
    Publication number: 20100148449
    Abstract: A labyrinth sealing ring for a labyrinth seal of a turbine disk 1 of a gas turbine includes a metallic annular element 3 with at least one annular sealing lip 4. The sealing lip 4 is provided with at least one groove 5 on its circumference which is essentially arranged in the radial direction.
    Type: Application
    Filed: December 2, 2009
    Publication date: June 17, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos GAEBLER
  • FAN CASING FOR A JET ENGINE
    Publication number: 20100150696
    Abstract: A fan casing (2) for a jet engine has a burst protection arrangement (7) made up of layers at least in an area of fan blades (5). To contain detached fan blades (5) within a fan casing (2) of a jet engine by use of a low-weight and easily manufacturable burst protection arrangement (7), the fan casing (2) is made of a fiber-composite material which itself forms at least one layer provided with at least one inorganic, non-metallic protective layer (8).
    Type: Application
    Filed: December 16, 2009
    Publication date: June 17, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Olaf Lenk
  • FLOW DIVIDER FOR A FAN ENGINE
    Publication number: 20100139241
    Abstract: A flow divider (1) for a fan engine which forms an annular leading edge (4) simultaneously on the outer circumference of an annular core air duct and the inner circumference of an annular secondary air duct, protrudes into the fan airflow and has an aerodynamic profile. In order to avoid blockage of the core air and/or secondary air ducts in the event of destruction or detachment of the flow divider (1), the flow divider features separable parts (6) which, whatever their orientation, are capable of passing the vane passages of the core air duct and the secondary air duct.
    Type: Application
    Filed: December 4, 2009
    Publication date: June 10, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Olaf LENK
  • FLUID FLOW MACHINE WITH SIDEWALL BOUNDARY LAYER BARRIER
    Publication number: 20100143140
    Abstract: A fluid flow machine has a main flow path in which at least one row of blades (2) is arranged, with at least one blade end of a blade row (2) being firmly connected to the main flow path confinement and, in an area of this fixed blade end at a sidewall (9), at least one longish, obstacle-type boundary layer barrier (11) is provided which in at least part of its course is oriented obliquely to the main flow direction, thereby deflecting fluid flowing near the sidewall towards the blade pressure side.
    Type: Application
    Filed: November 4, 2009
    Publication date: June 10, 2010
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker GUEMMER
  • METHOD AND APPARATUS FOR THE OPERATION OF A TURBOPROP AIRCRAFT ENGINE PROVIDED WITH PUSHER PROPELLERS
    Publication number: 20100139278
    Abstract: A method and an apparatus is disclosed for the operation of a turboprop aircraft engine provided with pusher propellers. In order to reduce thermal loading of the pusher propellers impaired by the hot exhaust-gas flow of the engine and increase the service life of the pusher propellers, cold air from the environment outside of the aircraft engine is fed into, and mixed with, the hot exhaust-gas flow passing the pusher propellers and their connecting structure before the hot exhaust-gas flow reaches the pusher propellers.
    Type: Application
    Filed: December 7, 2009
    Publication date: June 10, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten CLEMEN
  • METHOD FOR THE MANUFACTURE OF A WELDED ROTOR FOR A GAS-TURBINE ENGINE
    Publication number: 20100140230
    Abstract: With a method for manufacturing welded rotors for a turbine, especially a gas-turbine engine, in which two or more rotor disks are joined to each other by conventional welding processes using welds extending radially to the rotor axis and the weld zone is subsequently thermally treated at a certain temperature to relieve residual tensile stresses by relaxation, the weld is set to a significantly lower non-relaxatory temperature level than the heat-affected zone adjoining the weld so that, as a result of the high temperature gradient, a residual compressive stress or at least a substantially reduced residual tensile stress is impressed on the weld. Compared to conventionally heat treated and welded rotors, improved strength properties in the weld zone and an increased service life are obtained as a result of the reduced tensile stresses.
    Type: Application
    Filed: December 2, 2009
    Publication date: June 10, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl SCHREIBER, Kim GROSSMANN
  • METHOD FOR THE MANUFACTURE OF HYBRID COMPONENTS FOR AIRCRAFT GAS TURBINES
    Publication number: 20100126662
    Abstract: When manufacturing hybrid components, especially the fan blades or stator vanes of an aircraft gas turbine including a metallic enveloping structure and a supporting structure in fiber-composite material, the mating faces of the metallic structure are cleaned and roughened with plasma prior to fitting the fiber-composite material and the metallic molecules activated so that high attractive forces take effect and an intimate, extremely strong adhesive connection is produced between the metal and the fiber-composite material. Fan blades or stator vanes of the fan structure of a gas-turbine engine which are manufactured according to this method are capable of transmitting high loads and feature a long service life.
    Type: Application
    Filed: November 19, 2009
    Publication date: May 27, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Karl SCHREIBER
  • DEVICE FOR THE PREVENTION OF HIGH OIL TANK PRESSURES UNDER NEGATIVE G CONDITIONS
    Publication number: 20100126589
    Abstract: An aircraft gas-turbine oil tank has a breather outlet tube 2 branching off from an upper area of the oil tank 1 and connecting to a breather and a connecting tube 6 joining to a bottom area of the oil tank 1. An air guide tube which is open at both ends is arranged in the upper area of the oil tank 1, with the air guide tube 3 protruding into the breather outlet tube 2 and extending into a middle area of the oil tank 1.
    Type: Application
    Filed: September 9, 2009
    Publication date: May 27, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Robert ANGST
  • HYBRID COMPONENT FOR A GAS-TURBINE ENGINE
    Publication number: 20100129651
    Abstract: A hybrid component for a gas-turbine engine includes a supporting structure (2) in fiber-composite material and a metallic structure (3) intimately connected to the latter via a thin highly elastic intermediate layer (7) made of thermoplastic polyurethane. The highly elastic material not only provides for a firm connection between the metallic structure and the supporting structure, but also for an absorption of the in-service vibrations and a compensation of the different expansion behavior of the fiber-composite material and the metal. Furthermore, a concentrated load applied to the component by an impinging foreign body is converted by the highly elastic intermediate layer into an area load, thereby substantially reducing the hazard of damaging the supporting structure due to crack formation.
    Type: Application
    Filed: November 17, 2009
    Publication date: May 27, 2010
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl SCHREIBER