Patents Assigned to Rolls-Royce plc
  • Aircraft engine mounting
    Patent number: 7313920
    Abstract: An aircraft engine mounting assembly comprising a bracket arrangement with two plates located either side of an opening in the structural bypass duct. The bracket arrangement mounts two inclined links which connect to the engine. In normal usage, tension/compression from the links will be passed by the bracket arrangement into the airframe. Upon failure of one of the links the bracket arrangement will engage with the structural bypass duct to transmit engine loads into the airframe via the duct.
    Type: Grant
    Filed: December 2, 2004
    Date of Patent: January 1, 2008
    Assignee: Rolls-Royce plc
    Inventors: Richard G Stretton, Ewan F Thompson
  • Liner panel
    Publication number: 20070297910
    Abstract: A liner panel for a fan casing of a gas turbine engine comprises a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade failure. In use ice may be released from a fan blade in a first direction, and (in the case of a blade-off event) a fan blade or part of a fan blade may be released in a second direction. The panel is characterised in that its compressive strength is greater in the first direction than in the second direction such that the released ice will be deflected by the panel but the released fan blade or part of a fan blade will pass through the panel.
    Type: Application
    Filed: May 11, 2007
    Publication date: December 27, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventors: Clare Pool, Cedric Harper, Geoffrey Attewell
  • Aerofoil
    Publication number: 20070297898
    Abstract: An aerofoil made from a sheet metal blank which is bent in the shape of an aerofoil such that it has a leading edge, a trailing edge, a pressure side and a suction side, and the blank is joined at the trailing edge. The regions of the sheet metal blank that form the leading edge, trailing edge and pressure side of the aerofoil comprise a plurality of perforations. The suction side region of the sheet metal blank is imperforate.
    Type: Application
    Filed: May 17, 2007
    Publication date: December 27, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Sean A. Walters
  • Vane support in a gas turbine engine
    Patent number: 7311495
    Abstract: A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane 2 and the wall of the slot 8, 10. A restraint element 14, 34 is mounted in a recess 26, 28; 48 of the support structure 4, 6 and is engaged by a notch 30, 32 in the vane 2 to restrict axial displacement of the vane 2. Consequently, vibration of the vane in directions perpendicular to the lengthwise direction of the vane are damped by the elastomeric material 12 but bodily axial displacement of the vane 2 is prevented by the restraint elements 14, 34.
    Type: Grant
    Filed: June 30, 2006
    Date of Patent: December 25, 2007
    Assignee: Rolls-Royce PLC
    Inventors: Duncan E Ashley, Peter Allford, Martin Lawrence
  • Turbomachine blade
    Patent number: 7311500
    Abstract: A turbomachine blade comprising a root portion and an aerofoil portion, the aerofoil portion having a leading edge, a trailing edge, a concave metal wall portion extending from the leading edge to the trailing edge and a convex metal wall portion extending from the leading edge to the trailing edge. The concave metal wall portion and the convex metal wall portion form a continuous integral metal wall. The aerofoil portion has a hollow interior defined by at least one internal surface and the hollow interior of the aerofoil portion is at least partially filled with a vibration damping and stiffening system that comprises a vibration damping material. The vibration damping material is bonded to the at least one internal surface and the vibration damping and stiffening system comprises a variation of material properties between the wall portions.
    Type: Grant
    Filed: July 1, 2003
    Date of Patent: December 25, 2007
    Assignee: Rolls-Royce plc
    Inventors: Jem A Rongong, Geoffrey R Tomlinson
  • Balancing method
    Patent number: 7309211
    Abstract: A method of balancing a rotor, where the rotor comprises a plurality of holes, comprises the steps of measuring an imbalance of the rotor, identifying at least one characteristic dimension associated with at least one hole, identifying a change to the or each characteristic dimension to reduce the imbalance, and changing the or each characteristic dimension.
    Type: Grant
    Filed: November 21, 2005
    Date of Patent: December 18, 2007
    Assignee: Rolls-Royce plc
    Inventors: Stuart Ellis, Michael P Keenan
  • Method of manufacturing a hollow article
    Publication number: 20070286760
    Abstract: A method of manufacturing a hollow article (10) comprising the steps of cold pressing two members (30,34) to form at least one depression (32,36) in the members (30,34). Arranging the two members (30,34) in abutting relationship such that the at least one depression (32,36) defines at least one chamber between the two members (30,34). Sealing (41) the edges (40,42) of the two members (30,34) together to form a core structure (44). Positioning the core structure (44) in a mould (46) to define a cavity (48) between the external surface (50) of the core structure (44) and the internal surface (52) of the mould (46), the internal surface (52) of the mould (46) substantially defining the external shape of the hollow article (10). Filling the cavity (48) between the core structure (44) and the mould (46) with a powder material (54), sealing the open edge of the core structure (44) to the mould (46).
    Type: Application
    Filed: March 15, 2007
    Publication date: December 13, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Ewan F. Thompson
  • Internally cooled aerofoils
    Publication number: 20070286729
    Abstract: A shroudless, air cooled gas turbine blade has an internal structure including load-carrying members (36,38,40) that support the blade outer wall (10) and divide the blade interior into cooling passages (28,30,32,34). The dimensions of the structure in particular the load-carrying members (36,38,40) are chosen with respect to inward heat flow during operation to tend to reduce heat transfer from the outer wall (10) to the load-carrying members (36,38,40) and with respect to mass distribution in the structure to reduce centrifugal forces during operation.
    Type: Application
    Filed: August 22, 2005
    Publication date: December 13, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Michiel Kopmels
  • Work extraction arrangement
    Patent number: 7305832
    Abstract: A work extraction arrangement (10) comprises a cooling assembly (12) for cooling a gas to provide a working fluid capable of doing work. The arrangement (10) further includes storage means (14) for storing the working fluid and a turbine assembly (18) for extracting work from the working fluid. A fluid delivery assembly (16) is also provided to deliver the working fluid to the turbine assembly (18).
    Type: Grant
    Filed: December 10, 2004
    Date of Patent: December 11, 2007
    Assignee: Rolls-Royce plc
    Inventors: Paul Fletcher, James I Oswald
  • Reduction of co-efficient of friction to reduce stress ratio in bearings and gas turbine parts
    Patent number: 7306434
    Abstract: A rotor blade, a rotor disc (24) or load bearing assembly having at least one bearing surface (22) for contact with a corresponding bearing surface (28). At least one selected area of the bearing surface (30,32) which, in operation, is an area of alternating stress greater than about 50 MPa (peak to peak), is configured to have a co-efficient of friction lower than the remainder of the bearing surface (34). The selected area (30,32) having a co-efficient of friction lower than the remainder of the bearing surface (34) may be provided by the application of a dry film lubricant, with the remaining area(s) (34) of said bearing surfaces (22) being substantially free of the said coating.
    Type: Grant
    Filed: February 1, 2005
    Date of Patent: December 11, 2007
    Assignee: Rolls-Royce plc
    Inventor: Keith Christopher Goldfinch
  • Rotor unbalance correction
    Publication number: 20070277606
    Abstract: A rotor such as a blisk B is balanced by determining the extent of any static or couple unbalance when the rotor is rotated about a test axis X while supported at a location surface 10 at which the rotor is supported in normal use. The location surface 10 is then modified, for example by removing material in a final machining operation, to eliminate the unbalance. For example the swash of the surface 10 may be altered and/or modification may be made to other location features (11) in order to cause the rotor to rotate, in normal operation, about an axis which is eccentric to the test axis X.
    Type: Application
    Filed: May 15, 2007
    Publication date: December 6, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: William E. Robbins
  • Flow control systems
    Publication number: 20070277888
    Abstract: A flow control system (24) comprises a fluidic control device (26) having a main fluid path (34, 38) for a flow of fluid through the device, and a control fluid path (30) for a control flow of fluid through the device (24). At least part of the control fluid path coincides with at least part of the main fluid path (34, 38) to control the flow of fluid out of the fluidic control device (24). A valve (28) is associated with the control fluid path. The value (28) is movable between an open condition to allow fluid to flow along the control fluid path to effect the aforesaid control of the fluid flow out of the fluidic control device, and a closed condition to inhibit or prevent fluid flow along the control fluid path (30).
    Type: Application
    Filed: March 15, 2007
    Publication date: December 6, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Timothy Scanlon
  • Temperature measuring system
    Patent number: 7303331
    Abstract: A temperature measuring system, comprising an imaging device for focusing radiation towards a radiation detector, wherein the imaging device is a diffractive optical device.
    Type: Grant
    Filed: July 8, 2005
    Date of Patent: December 4, 2007
    Assignee: Rolls-Royce plc
    Inventor: Harold Heyworth
  • Calibration block
    Publication number: 20070271995
    Abstract: A calibration block for use in calibrating a thickness gauge having a diameter d, wherein the block has a measurement face and a recess extending inwardly of the block from a face opposite the measurement face, the recess having a maximum transverse dimension at the opposite face which is not less than 3 d, and in that the bottom of the recess is inclined relative to the measurement face in all directions from a central region of the bottom of the recess, the measurement face comprising a reference feature, the location of which corresponds to a specific point on the bottom of the recess.
    Type: Application
    Filed: April 25, 2007
    Publication date: November 29, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Nicholas B. Orchard
  • Thrust correction
    Publication number: 20070276601
    Abstract: In a method for determining the free field thrust of a gas turbine engine the gas turbine engine is attached to a movable support means in an enclosed gas turbine engine test facility, and is operated at a selected engine operating point. The thrust applied by the engine to the thrust cradle is measured via thrust measurement means. Calculations are performed to determine the gas turbine engine intake momentum drag generated by airflow into the gas turbine engine intake, the thrust cradle drag force generated by airflow past the moveable support means of the thrust cradle, the base drag generated as a result of accelerating nozzle ejector airflow, a pre-stream tube force related to turning of stream lines in the intake air path, a pre-stream tube force related to a bell mouth pull-off force.
    Type: Application
    Filed: May 23, 2007
    Publication date: November 29, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventors: Robert N. Parfitt, Martin R. Turville, Maurice C. Bristow, Stephen G. Brown
  • Magnetic bearings
    Patent number: 7301252
    Abstract: A magnetic bearing (1, 2, 3) has two bearing members (5, 7) each of which carries a set of bearing elements (4, 6) and the bearing elements (4) of a said set carried by one member (5) interleaved with the bearing elements (6) of a said set carried by the other member (7) to define three or more substantially parallel interleaf gaps (11) between successive elements (4, 6, 4, . . . ) so that bearing forces can be developed as a result of magnetic shear stresses acting across those gaps (11). The magnetic bearing achieves its bearing forces as the sum of force contributions from a number of parallel (or nearly-parallel) airgaps (11) and each of these individual airgap force contributions comes about as the integration of magnetic shear stress over the airgap area brought about by causing lines of magnetic flux to cross the airgap at an angle to the normal.
    Type: Grant
    Filed: July 11, 2001
    Date of Patent: November 27, 2007
    Assignee: Rolls-Royce PLC
    Inventor: Seamus Dominic Garvey
  • Aircraft engine mounting assembly
    Patent number: 7296414
    Abstract: A mounting assembly (10) for mounting a gas turbine engine on an aircraft. The assembly (10) comprising four equispaced hydraulic piston and cylinder thrust links (16) connecting between the engine fan case (12) and the air intake (14), which intake (14) is mounted to the airframe.
    Type: Grant
    Filed: October 1, 2004
    Date of Patent: November 20, 2007
    Assignee: Rolls-Royce plc
    Inventors: Richard G Stretton, Peter K Beardsley, David M Beaven
  • Apparatus for forming a body
    Publication number: 20070262122
    Abstract: An atmospheric shield for isolating a component from an external atmosphere is provided and comprising an envelope, and a base carrying a continuous channel, wherein the base and the envelope are arranged to define an enclosure within which the component to be isolated in use is located and such that a portion of the envelope extends within the continuous channel, wherein a seal is provided within the channel to seal between the envelope and the base.
    Type: Application
    Filed: May 11, 2007
    Publication date: November 15, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventors: Daniel Clark, Jeffrey Allen
  • Aeroengine noise reduction
    Publication number: 20070251212
    Abstract: A gas turbine engine comprising an afterbody, which extends rearwardly from a nozzle exit plane, having an outer surface comprising acoustic liners.
    Type: Application
    Filed: March 28, 2007
    Publication date: November 1, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Brian J. Tester
  • Cooled gas turbine aerofoil
    Publication number: 20070253815
    Abstract: An internal fluid cooling system for a gas turbine aerofoil (2) comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage (50,52,54 & 48,56,58) in the interior of the aerofoil (2). The cooling fluid—in particular air—is supplied to an inlet end (22,24) of each passage (50,52,54 & 48,56,58) and exhausted through a multiplicity of discharge holes (60,62,64,68) to provide tip, leading edge, trailing edge and surface film cooling. The inlet end (22) of a first serpentine passage (50,52,54) is positioned close to the leading edge (26) and flows rearwards while the inlet end (24) of the second serpentine passage (48,56,58) is positioned close to the trailing edge (28) and flows forwards.
    Type: Application
    Filed: August 22, 2005
    Publication date: November 1, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventors: Michiel Kopmels, Ian Tibbott, Edwin Dane, Mark Mitchell