Patents Assigned to Rolls-Royce Deutschland Ltd & Co KG
  • MULTI-VANE VARIABLE STATOR UNIT OF A FLUID FLOW MACHINE
    Publication number: 20100124487
    Abstract: A fluid flow machine has a main flow path which is confined by a hub (3) and a casing (2) and in which at least one row of variable stator vanes (1) is arranged. The stator vanes (1) are rotatably borne around a rotary axis 4. On at least one of the hub (3) and the casing (2), at least one arrangement with at least two stator vanes (1) connected to a common rotary base (5) is provided, such that the at least two stator vanes (1) are rotatable around the rotary axis (4) when this multi-vane variable stator unit is varied.
    Type: Application
    Filed: October 30, 2009
    Publication date: May 20, 2010
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker GUEMMER
  • OIL SYSTEM HEATING FOR AIRCRAFT GAS TURBINES
    Publication number: 20100122518
    Abstract: An oil pre-heating apparatus for an aircraft gas turbine has a suction line 2 connectable to an oil tank 1 of an aircraft gas turbine, with a heat source 3 connected to the suction line 2 and operated independently of the aircraft and with a return line 4 connected to the heat source 3 and connectable to the oil tank 1.
    Type: Application
    Filed: November 17, 2009
    Publication date: May 20, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Robert ANGST
  • ENGINE SHAFT IN THE FORM OF A FIBER-COMPOSITE PLASTIC TUBE WITH METALLIC DRIVING AND DRIVEN PROTRUSIONS
    Publication number: 20100113171
    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: Application
    Filed: November 5, 2009
    Publication date: May 6, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl SCHREIBER, Raimund GROTHAUS
  • ENGINE SHAFT FOR A GAS-TURBINE ENGINE
    Publication number: 20100113170
    Abstract: A low-pressure turbine shaft (11) for a gas-turbine engine includes a fiber-composite plastic tube (13) with fiber layers provided in an inner wall area for taking up and transmitting torsional forces, and, in an outer wall area, with fiber layers suitably oriented for influencing stiffness and damping characteristics. The fiber layers are embedded in a high temperature resistant plastic matrix. A load input element (14) is an attachment flange (24) made of fiber-composite plastic material integrally formed on a fiber-composite plastic tube (13). A load output element (15) is a metallic driven protrusion inseparably connected to the fiber layers transmitting the torsional forces. Alternatively, the load input element may be provided as a metallic driving protrusion, which is firmly connected to the fiber layers taking up the torsional forces.
    Type: Application
    Filed: November 5, 2009
    Publication date: May 6, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl Schreiber, Raimund Grothaus
  • METHOD FOR THE MANUFACTURE OF AN ENGINE SHAFT
    Publication number: 20100109184
    Abstract: For the manufacture of a tubular low-pressure turbine shaft made of a fiber-composite material with metallic driven/driving protrusions (2) attached to its ends, the fiber material is wound onto a winding core (4) provided in the form of a closed tube and made of high-strength material and onto a conically tapered adapter (3) formed on the driven/driving protrusion. By expanding the winding core with a pressurized liquid medium, the fiber material embedded in a synthetic resin is compacted as a function of the design of the winding body and the liquid pressure. Upon curing of the synthetic resin at elevated temperature the winding core is pressure-relieved and removed with reduced diameter.
    Type: Application
    Filed: November 5, 2009
    Publication date: May 6, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl SCHREIBER, Raimund GROTHAUS
  • HUB CONE FOR AN AIRCRAFT ENGINE
    Publication number: 20100111702
    Abstract: A hub cone (20, 30, 40) is provided for an aircraft engine having a propeller (2, 32, 42) or a blower (fan) (3) enveloped by a casing (5). To reduce flow losses of the hub cone and increase efficiency of the engine, a contour of the hub cone is described by the following equation: S(x)=Rmax*{1?[(x?Lmax)/Lmax]2}1/M; where: S(x) is a shape of the cone defined along the machine axis x; Rmax is a maximum extension (26) of the cone in the radial direction; Lmax is a maximum extension (25) of the cone in the direction of the machine axis x and M is a quantity describing the shape S(x).
    Type: Application
    Filed: November 2, 2009
    Publication date: May 6, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten CLEMEN
  • Bore serration for locking threaded inserts against rotation
    Patent number: 7704028
    Abstract: A bore serration for locking externally serrated inserts (3) against rotation, with the external serration (4) comprising several teeth (5), and particularly for use with components made of hard, brittle materials, includes an arcuate serration (10) featuring arcuate recesses (7) produced by plunge or circumferential surface milling. Each of the recesses positively accommodates at least two teeth (5) of the outer serration (4) of the threaded insert (3). The arcuate serration can be produced with high dimensional accuracy without damaging the workpiece and with reduced wear of the tool, and ensures a long service-life of the threaded insert.
    Type: Grant
    Filed: May 8, 2008
    Date of Patent: April 27, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Rainer Mielke
  • Method and tooling for machining the annulus of gas-turbine rotor provided with integrally formed-on blades
    Patent number: 7704021
    Abstract: With an integrally bladed rotor, material removal is performed from the annulus (5) on a wide, even machining path (8) using the front-side cutting area of an essentially cylindrical cutter head (7). The tool shank (9) is shaped and dimensioned such that it does not collide with the opposite lateral surfaces of the differently curved and twisted blades (4). This type of machining enables an essentially even, smooth annulus surface to be obtained with a reduced number of overlapping machining paths (8). The time required for machining the annulus and the tool wear are reduced. With an annulus machined in accordance with the present invention, the rotor will satisfy high requirements on aerodynamics.
    Type: Grant
    Filed: February 19, 2009
    Date of Patent: April 27, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Jan Hollmann, Gregor Kappmeyer
  • FLUID FLOW MACHINE WITH PERIPHERAL ENERGIZATION NEAR THE SUCTION SIDE
    Publication number: 20100098527
    Abstract: A fluid flow machine has a main flow path (“MFP”) 2 with a blade row 5 therein, a blade end of a blade row being connected to the MFP confinement and a peripheral chamber 7 arranged near this blade end outside the MFP confinement. An outlet 6 is arranged near the fixed blade end near a blade suction side can issue fluid from peripheral chamber 7 onto the surface of the MFP confinement into the MFP. The fluid jet is oriented essentially tangentially to the contour of the MFP confinement when viewed in the meridional plane (x-r plane) and essentially parallel to the local tangent to the skeleton line of the nearest profile, when viewed in the plane established by circumferential direction u and meridional direction m.
    Type: Application
    Filed: October 8, 2009
    Publication date: April 22, 2010
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker GUEMMER
  • COMPRESSOR FOR A GAS TURBINE
    Publication number: 20100098530
    Abstract: A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement (20) between the shroud (8) and rotor hub (3) is formed by a discharge arrangement (23) for leakage air.
    Type: Application
    Filed: October 9, 2009
    Publication date: April 22, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten CLEMEN, Jens ORTMANNS
  • FLUID FLOW MACHINE WITH RUNNING GAP RETRACTION
    Publication number: 20100098536
    Abstract: A fluid flow machine includes a main flow path which is confined by a hub (3) and a casing (1) and in which at least one row of blades (5) is arranged, with a blade end with gap being provided on the blade row, with the blade end and the main flow path confinement performing a rotary movement relative to each other in a vicinity of the blade end, with at least part of the running gap (11) retracted radially from the main flow path confinement into the main flow path, with the running gap (11) at the retractions no longer being confined by the main flow path confinement, but by a peripheral guiding device (10) passed by the main flow and firmly connected to the main flow path confinement and having a row of profiles (12).
    Type: Application
    Filed: August 20, 2009
    Publication date: April 22, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Volker GUEMMER
  • Fuel injection device for an aircraft gas turbine
    Patent number: 7694899
    Abstract: A fuel injection device for fuel injection systems, e.g. for aircraft gas turbines, includes at least one fuel injection opening, through which a continuous flow of fuel 1 is issued, with the fuel injection opening having a non-circular cross-section.
    Type: Grant
    Filed: July 13, 2007
    Date of Patent: April 13, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Jeffrey-George Gerakis, Leif Rackwitz
  • INTAKE CONE FOR A GAS-TURBINE ENGINE
    Publication number: 20100051112
    Abstract: An intake cone for a gas-turbine engine has an essentially conical body 5 located on a retaining ring 3 connected to a fan rotor disk, with the body 5 being designed as one piece over its axial length and connected at a conical locating area to a rigidly designed conical supporting area borne on a fan rotor disk.
    Type: Application
    Filed: August 31, 2009
    Publication date: March 4, 2010
    Applicant: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Martina DIELING
  • FLUID FLOW MACHINE
    Publication number: 20100034637
    Abstract: A fluid flow machine has a main flow path 2 which is confined by a hub 3 and a casing 1 and in which at least one row of blades 5 is arranged. A gap 11 is provided on at least one blade row 5 between a blade end and a main flow path confinement, with the blade end and the main flow path confinement performing a rotary movement relative to each other. At least one reversing duct 7 is provided in the area of the blade leading edge in the main flow path confinement at a discrete circumferential position. The reversing duct 7 connects two openings 12, 13 arranged on the main flow path confinement.
    Type: Application
    Filed: August 3, 2009
    Publication date: February 11, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Volker Guemmer
  • Method and device for the finish machining of gas-turbine engine blades cast in a brittle material
    Patent number: 7658004
    Abstract: For the finish machining of turbine blades cast in titanium aluminide, the feeders (3) and runner portions (6) yielded by the casting process remain on the blade and serve as auxiliary clamping structure for clamping the blade to the workpiece carrier (15). In a position corresponding to the reference points for machining, clamping surfaces (12) with conical recesses (13), followed by threaded holes (14) are produced on the runners. For clamping the workpiece to a workpiece carrier (15), spring-loaded taper centering sleeves (18) arranged in the workpiece carrier or clamping bolts (21), respectively, engage the conical recesses and threaded holes, to enable the blade to be clamped and machined by way of the auxiliary clamping structure in the position corresponding to the reference points.
    Type: Grant
    Filed: December 20, 2006
    Date of Patent: February 9, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Rainer Mielke
  • Lean premix burner with circumferential atomizer lip
    Patent number: 7658075
    Abstract: With a lean premix burner (1), a plurality of preferably V-shaped, closely spaced fuel channels (12) is formed into the circumferential fuel-supplied film application surface (8) of the atomizer lip (9) in the direction of flow, in order to achieve a better heat transfer to the fuel due to the uniform fuel distribution and a transverse flux in the plurality of small fuel flows caused by the Marangoni effect, to completely converse the fuel by early vaporization and improved spraying, to reduce nitrogen oxide emission and to suppress combustion-driven pressure oscillations.
    Type: Grant
    Filed: December 18, 2006
    Date of Patent: February 9, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Ralf Sebastian von der Bank
  • METHOD FOR THE MANUFACTURE OF METALLIC COMPONENTS
    Publication number: 20100024214
    Abstract: When manufacturing slender metallic components (9) by cutting shaping from pre-manufactured forgings (1), the respective component (9) upon finish machining by cutting is dimensionally inspected to determine deformations (a) induced by manufacture, as compared to the nominal position, and on the basis of the measuring result the position of tensile stress areas (4) in rim layers of the component (9) is determined. For positionally balancing the component (9), the tensile stress areas (4) causing deformation of the component (9) are subjected to controlled shot peening at a specified intensity.
    Type: Application
    Filed: July 27, 2009
    Publication date: February 4, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Rainer MIELKE
  • Gas-turbine combustion chamber with air-introduction ports
    Patent number: 7654089
    Abstract: This invention relates to a gas-turbine combustion chamber with at least one pilot burner (2) and at least one main burner (3) which are axially and radially offset relative to each other, said combustion chamber (1) comprising an outer flame-tube wall (4) and an inner flame-tube wall (5) each provided with ports for the introduction of air, and said main burner (3) being located at the outer flame-tube wall (4) and said pilot burner (2) being located at the inner flame-tube wall (5), characterized in that the outer flame-tube wall (4) is provided with a first arrangement (6) of ports and in that the inner flame-tube wall (5) is provided with a second arrangement (7) of ports.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: February 2, 2010
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Schilling, Thomas Dörr
  • METHOD FOR IMPROVING THE FLOW CONDITIONS ON THE PROPELLER OR FAN OF AN AIRCRAFT ENGINE AND ACCORDINGLY DESIGNED HUB CONE
    Publication number: 20100021310
    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: Application
    Filed: July 23, 2009
    Publication date: January 28, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten CLEMEN
  • GAS-TURBINE ENGINE WITH VARIABLE STATOR VANES
    Publication number: 20100014960
    Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).
    Type: Application
    Filed: July 6, 2009
    Publication date: January 21, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Stuart LEE