Patents Assigned to Rolls-Royce plc
  • Multiple layer erosion resistant coating and a method for its production
    Patent number: 5952085
    Abstract: A multiple layer erosion resistant coating on a substrate comprises alternate layers of tungsten and titanium diboride. All of the layers have the same thickness and preferably have thickness's of between 0.3 and 1 micrometer to give improved erosion resistance. The layers are produced by spattering.
    Type: Grant
    Filed: February 6, 1997
    Date of Patent: September 14, 1999
    Assignees: Rolls-Royce plc, Turbomeca Societe Dite, Etat Francais
    Inventors: David S. Rickerby, Pierre Monge-Cadet, Guy Farges
  • Method of making a fibre reinforced metal component
    Patent number: 5946801
    Abstract: A ceramic fibre reinforced metal rotor is manufactured from a first metal ring, a second metal ring and a plurality of fibre preforms. Each fibre preform includes a metal coated ceramic fibre arranged in a spiral. An annular groove is formed in an axial face of the first metal ring and the fibre preforms are arranged in the annular groove. An annular projection is formed on an axial face of the second metal ring and two annular grooves are formed on opposite radial sides of the annular projection. The second metal ring is arranged such that the annular projection is aligned with the annular groove of the first metal ring. Heat and pressure is applied to axially consolidate the fibre preforms and to bond the first metal ring, the second metal ring and the fibre preforms to form a unitary composite component. The grooves allow axial movement of the projection and control consolidation.
    Type: Grant
    Filed: September 11, 1997
    Date of Patent: September 7, 1999
    Assignee: Rolls-Royce plc
    Inventors: Edwin S Twigg, Charles R Talbot, Phillip J Doorbar
  • Bearing assembly and split bearing race for use in the same
    Patent number: 5944429
    Abstract: A bearing assembly supports a shaft. The bearing assembly comprises an outer bearing race and an inner bearing race. Each bearing race has a race track in which a plurality of rolling elements are located. The inner bearing race is split into two halves. The two halves of the split bearing race are interconnected by curvic teeth. The curvic teeth constrain relative movement between the two halves of the split bearing race and maintain concentricity of the bearing race.
    Type: Grant
    Filed: April 30, 1997
    Date of Patent: August 31, 1999
    Assignee: Rolls-Royce plc
    Inventor: James P Berry
  • Ice protection for porous structure
    Patent number: 5944287
    Abstract: A nacelle having a porous structure is provided with laminar flow control and contamination protection. In region B suction through a composite layer is achieved by evacuating a chamber adjacent the inner surface of the nacelle to provide laminar flow control. At the leading edge of the nacelle a sintered metal sheet is attached to an inner surface of the composite layer to control the flow of a liquid over the leading edge of the nacelle. The liquid is contained in a chamber adjacent the sintered metal sheet which is defined by a backing sheet which has a series of depressions therein. Hot air fed through a perforated pipe impinges upon the backing sheet and the depressions transmit heat to the sintered metal sheet. The sintered metal sheet has good thermal conductivity and in turn heats the porous composite layer to prevent the formation of ice thereon.
    Type: Grant
    Filed: June 12, 1997
    Date of Patent: August 31, 1999
    Assignee: Rolls-Royce plc
    Inventor: Leonard J Rodgers
  • Gas turbine engine turbine system
    Patent number: 5941687
    Abstract: When cooling air from a gas turbine engine compressor is supplied in greater quantities than is needed, the flow thereof is reduced firstly and mainly by ensuring that the air leaves a blade stage cooling thereby at a radius less than that of its entry. A pressure head results which slows the cooling air flow rate prior to its entering a plenum chamber defined by the disc of the stage and fixed structure. There is a reduced tendency of the air to enter the gas stream.
    Type: Grant
    Filed: October 16, 1997
    Date of Patent: August 24, 1999
    Assignee: Rolls-Royce plc
    Inventor: Henry Tubbs
  • Gas turbine engine support structure
    Patent number: 5941683
    Abstract: A bearing support structure for a gas turbine engine comprises an annular array of stator vanes and a radially inner bearing support portion which are interconnected by an annular array of radially extending U-shaped cross-section parts. The U-shaped cross-section parts are interconnected at their radially outer extents and are arranged so that adjacent parts are open in generally opposite axial directions. Such a bearing support structure can carry service pipes with good accessibility and be produced by casting, thereby reducing its cost.
    Type: Grant
    Filed: February 17, 1998
    Date of Patent: August 24, 1999
    Assignee: Rolls-Royce plc
    Inventors: Philip Ridyard, Alan G Foster
  • Thermal barrier coating for a superalloy article and a method of application thereof
    Patent number: 5942337
    Abstract: A multi-layer thermal barrier coating (42) for a superalloy article (40) comprises a platinum enriched superalloy layer (44), an MCrAlY bond coating (46) on the platinum enriched superalloy layer (44), a platinum enriched MCrAlY layer (48) on the MCrAlY bond coating (46), a platinum aluminide coating (50) on the platinum enriched MCrAlY layer (48), an oxide layer (54) on the platinum aluminide coating (50) and a ceramic thermal barrier coating (56) on the oxide layer (54). The platinum aluminide coating (50) and the platinum enriched MCrAlY layer (48) reduce movement of transition metals from the superalloy substrate (40) and the MCrAlY bond coating (46) to the oxide layer (54) so that the oxide layer is very pure alumina.
    Type: Grant
    Filed: June 5, 1997
    Date of Patent: August 24, 1999
    Assignees: Rolls-Royce, PLC, Chromalloy United Kingdom Limited
    Inventors: David S Rickerby, Rodney G Wing
  • Gas turbine engine fan blade retention
    Patent number: 5913660
    Abstract: A fan for a gas turbine engine comprises a rotary disc carrying an annular array of radially extending fan blades. Each fan blade has a root portion which is radially constrained within a generally axially extending groove formed within a disc rim. The blade root comprises two portions each radially convergent toward one another with respect to the axis of rotation of the disc. The groove within the disc also comprises two base portions each being correspondingly radially convergent toward one another. Axial retention of the blade root within the groove is achieved by the centrifugal component of the blade load acting in an opposite direction to any applied axial load in the forward or rearward direction.
    Type: Grant
    Filed: July 1, 1997
    Date of Patent: June 22, 1999
    Assignee: Rolls-Royce PLC
    Inventor: David S Knott
  • Gas turbine engine starting
    Patent number: 5911678
    Abstract: A gas turbine engine is provided with an air supply adapted to provide air to an engine starter system. The engine is also provided with an oil based lubrication system and control system. The control system is adapted to provide oil to the lubrication system under pressure from the starter air supply.
    Type: Grant
    Filed: July 13, 1998
    Date of Patent: June 15, 1999
    Assignee: Rolls-Royce plc
    Inventor: Cyril M. White
  • Gas turbine engine casing
    Patent number: 5899660
    Abstract: A gas turbine engine casing includes a plurality of coaxially interconnected ring members each provided with a flange at each of their axial extents to facilitate interconnection of the ring members by bolts; each ring member is provided with an integral array of inwardly directed stator vanes and carries an abradable sealing material to cooperate with the tips of rotor blades of the engine.
    Type: Grant
    Filed: April 18, 1997
    Date of Patent: May 4, 1999
    Assignee: Rolls-Royce plc
    Inventor: Alec G Dodd
  • Nickel alloy for turbine engine components
    Patent number: 5897718
    Abstract: A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.
    Type: Grant
    Filed: April 16, 1997
    Date of Patent: April 27, 1999
    Assignee: Rolls-Royce plc
    Inventors: Steven J Hessell, Wayne Voice, Allister W James, Sarah A Blackham, Colin J Small, Michael R Winstone
  • Rotors for gas turbine engines
    Patent number: 5890874
    Abstract: A rotor for a ducted fan gas turbine engine includes a rotor disc on which a number of circumferentially spaced apart blades are mounted. Wall members are positioned to bridge the space between adjacent blades. The wall members correspond in profile with the blades adjacent thereto. A seal is mounted on a side face of each wall member and is bonded to a flexible mounting which is bonded itself to the wall member. The flexible mounting has elastic properties so as to allow the seal to deflect relative to the wall member under centrifugal loading during operation.
    Type: Grant
    Filed: January 7, 1997
    Date of Patent: April 6, 1999
    Assignee: Rolls-Royce plc
    Inventors: David M Lambert, David S Knott, Peter R Beckford
  • Process and apparatus for reading a dot matrix code marking on an article
    Patent number: 5892846
    Abstract: A process and associated apparatus can automatically read a dot matrix code marking on an article even when the marking has been partly obscured or damaged in some way. The process comprises capturing a video image of the dot matrix code and correlating points on the captured image with a mask of expected dot appearance, using a known two-dimensional correlation technique. However, the correlation is performed in accordance with certain thresholding and mask adjustment criteria to improve read reliability and map the possible dot pattern in preparation for an attempt at reading the code. After automatically reorientating the map of possible dots to a read orientation if necessary, decoding of the pattern of possible dots is then attempted by comparing it with a datum grid representing rows and columns of valid dot matrix codes. The process can output a signal affirming that a valid code has been found.
    Type: Grant
    Filed: February 28, 1996
    Date of Patent: April 6, 1999
    Assignee: Rolls-Royce plc
    Inventor: Neil A. Davis
  • Gas turbine engine rotor disc with cooling fluid passage
    Patent number: 5888049
    Abstract: A gas turbine engine rotor disc (20) is provided with a plurality of cooling air supply passages (32) which are generally radially extending but are inclined in the downstream direction. Each passage (32) has a cross-sectional configuration which renders the ends (34) of the passages (32) less likely than normal to act as the site of hoop-stress induced cracks.
    Type: Grant
    Filed: June 9, 1997
    Date of Patent: March 30, 1999
    Assignee: Rolls-Royce plc
    Inventors: Peter Broadhead, John Hoptroff, Peter Avery
  • Control system for a ducted fan gas turbine engine
    Patent number: 5887419
    Abstract: If the fan of a ducted fan gas turbine engine is damaged, the power output of the engine may not be sufficient for a given throttle setting. The present invention provides a control system which detects fan damage and ensures that there is sufficient fuel flow to the engine to ensure that the overall engine power output is consistent with that commanded by the throttle setting.
    Type: Grant
    Filed: October 30, 1997
    Date of Patent: March 30, 1999
    Assignee: Rolls-Royce plc
    Inventors: Arthur L Rowe, Nikolaus Kurz
  • Gas Turbine engine casing construction
    Patent number: 5885056
    Abstract: Casing assembly for a gas turbine engine comprising an annular cross section casing around which a plurality of layers of flexible material are wound. One or more rigid panels are positioned between the wound flexible material and the annular casing. The rigid panel provides enhanced containment of a detached fan blade or part of a fan blade by distributing the load of the detached blade across the wound flexible material.
    Type: Grant
    Filed: March 6, 1997
    Date of Patent: March 23, 1999
    Assignee: Rolls-Royce plc
    Inventor: Jeremy P Goodwin
  • Fuel system for a gas turbine engine
    Patent number: 5884483
    Abstract: A staged fuel system for a gas turbine engine in which the main burners are supplied with fuel through fluid pressure actuated, servo-controlled valves. All pilot and main burners are supplied from a single manifold. However, fuel flow to the main burners is controlled by the servo-valves which are controlled by pressure in a servo-manifold fed with fuel tapped from a high pressure region of the fuel system. Thus, a simple variable control valve on the outlet of the servo-manifold is able to control fuel staging.
    Type: Grant
    Filed: April 16, 1997
    Date of Patent: March 23, 1999
    Assignee: Rolls-Royce plc
    Inventor: Kevin M Munro
  • Multiple layer erosion resistant coating and a method for its production
    Patent number: 5876572
    Abstract: A multiple layer erosion resistant coating on a substrate comprises alternate layers of tungsten and titanium diboride. All of the layers have the same thickness and preferably have thickness's of between 0.3 and 1 micrometer to give improved erosion resistance. The layers are produced by sputtering.
    Type: Grant
    Filed: February 6, 1997
    Date of Patent: March 2, 1999
    Assignees: Rolls-Royce plc, Turbomeca Societe Dite
    Inventors: David S. Rickerby, Pierre Monge-Cadet, Guy Farges
  • Tip clearance control
    Patent number: 5871333
    Abstract: A tip clearance control system operated by differential air pressure has a movable shroud liner segment assembly which forms the inner circumference of an annular pressure chamber encircling the blades of a rotary stage. High pressure air is bled into the chamber from a source of HP compressor delivery air through small holes. The chamber may be vented rapidly through an electrically controlled valve into the engine bypass duct. When the valve is opened pressure in the chamber is dropped quickly below gas path pressure to move the shroud liner segments radially outwards thereby increasing blade tip clearance.
    Type: Grant
    Filed: April 28, 1997
    Date of Patent: February 16, 1999
    Assignee: Rolls-Royce PLC
    Inventor: Robin W P Halsey
  • Method of investment casting and a method of making an investment casting mould
    Patent number: 5868194
    Abstract: A method of making an investment casting mould comprises producing a CAD definition of a turbine blade, and determining the distribution of isosurfaces of constant temperature around the CAD definition of the at least one article if the external surface of the CAD definition of the at least one article was at a high temperature (Thigh). One of the isosurfaces of constant temperature is selected to define the external shape and the thickness of an investment casting mould. A pattern of the turbine blade is produced from the CAD definition of the turbine blade. The investment casting mould is made with an internal shape defined by the pattern of the turbine blade and an external shape and thickness distribution defined by the selected isosurface of constant temperature. The pattern is then removed from the investment casting mould.
    Type: Grant
    Filed: January 23, 1997
    Date of Patent: February 9, 1999
    Assignee: Rolls-Royce plc
    Inventor: Dominic J. Horwood