Patents Assigned to Rolls-Royce plc
  • Ceramic core bodies
    Publication number: 20060223019
    Abstract: Firing of ceramic cores (1) is important in order to achieve manufacturing processes. These ceramic cores (1) are generally formed in a “green” state which has limited mechanical strength and may be distorted during the firing process by non-uniform thermal effects, etc. By providing a tube or containment 2 which is located on a saggar base 3 and surrounded by firing media 4, it is possible to achieve an initial pre-firing step whereby the “green” state core 1 is located through a stem 1a in an initial partial depth 5 of firing media 4 in the tube or containment 2 until it achieves a sufficient mechanical strength to enable positional adjustment. Thus, the green core will be pre-fired in a kiln solely supported through the stem 1a and then the core adjusted using a tool such as an engineering rule.
    Type: Application
    Filed: March 6, 2006
    Publication date: October 5, 2006
    Applicant: ROLLS-ROYCE PLC
    Inventors: Jamie McGourlay, Bhupendra Prajapati
  • Core leaching
    Publication number: 20060219664
    Abstract: Removal of a soluble part of a core allows provision of relatively complex three-dimensional geometric shapes in a component. Unfortunately previous leaching arrangements have been relatively erratic such that it is difficult to provide consistency of component form over a batch of components formed. By providing a tank combination which comprises typically a number of dip tanks, it is possible to provide consistency in terms of leach solution efficiency upon cores. Generally leaching solution held within the tanks is adjusted through either a prior calibrating adjustment tank or through agitation or other means in the tank such that the effects of saturation ageing of the leaching solution can be homogenised across all cores subject to the leaching process.
    Type: Application
    Filed: March 6, 2006
    Publication date: October 5, 2006
    Applicant: Rolls-Royce plc
    Inventor: Jamie McGourlay
  • Intake duct
    Publication number: 20060223429
    Abstract: An intake duct for a compressor comprises an inlet and an outlet means. The duct has a serpentine path. The outlet means comprises a first outlet and a second outlet. The duct further comprises at least one grille member configured to prevent the passage of objects over a predetermined size which is positioned in the duct out of the line of sight when viewed through the inlet. The duct is shaped such that in operation objects passing through the at least one grille member greater than a predetermined mass are directed towards the first outlet and the remainder of the objects are directed towards the second outlet. The first outlet leads overboard and/or to a trap and the second outlet leads to a compressor.
    Type: Application
    Filed: December 16, 2005
    Publication date: October 5, 2006
    Applicant: ROLLS-ROYCE PLC
    Inventors: Alec Groom, John Hacker, Jonathan Wilson, Gareth Jones
  • Vane assembly for a gas turbine engine
    Patent number: 7114917
    Abstract: An exhaust diffuser unit for a gas turbine engine includes an outer ring, a diffuser cone and vanes, all made from a ceramic matrix composite material. Each vane has end components which have apertures through which a metallic support strut extends. The support strut is rigidly secured at its radially outer end to a diffuser casing, and is slidably but non-rotatably received at its radially inner end in an aperture in a boss provided on a drum. Structural loads between the casing and the drum are transferred through the strut independently of the vane. Gas loads on the vane are transferred to the strut by way of metallic end components.
    Type: Grant
    Filed: June 4, 2004
    Date of Patent: October 3, 2006
    Assignee: Rolls-Royce plc
    Inventor: David Thomas Legg
  • Combustor
    Publication number: 20060213203
    Abstract: A casing for a combustor of a gas turbine engine has a plurality of apertures, each aperture being reinforced with a band of material dividing the aperture. The casing and reinforcing member are forged simultaneously with the reinforcing member aligned with the direction of maximum stress field.
    Type: Application
    Filed: November 1, 2005
    Publication date: September 28, 2006
    Applicant: ROLLS-ROYCE PLC
    Inventor: Stephen Cooper
  • Composite blade
    Publication number: 20060216154
    Abstract: A composite blade (28) comprises a root portion (38) and an aerofoil portion (40). The aerofoil portion (40) has a tip (50) remote from the root portion (38). The aerofoil portion (40) has a leading edge (42), a trailing edge (44), a suction surface (46) extending from the leading edge (42) to the trailing edge (44) and a pressure surface (48) extending from the leading edge (42) to the trailing edge (44). The composite blade (28) comprises reinforcing fibres (62) arranged in a matrix material (63). The tip (50) of the aerofoil portion (40) is arranged to define a recess (66), an insert (68) is arranged in the recess (66) and the insert (68) comprises an abradable material.
    Type: Application
    Filed: November 23, 2005
    Publication date: September 28, 2006
    Applicant: ROLLS-ROYCE PLC
    Inventor: Alison McMillan
  • Blades
    Patent number: 7112044
    Abstract: Percussive impacts due to bird strikes upon the hollow fan blades 20 are a well known problem. These percussive impacts not only deform previous fan blades but also reduce their stiffness. In accordance with the present invention, hollow fan blades 20 incorporate a cavity 23 within which, a matrix 24 with embedded expandable elements 25, is located. Thus, upon a percussive impact these expandable elements 25 are released in order to create an internal pressure within the cavity 25 which acts outwardly in order to relieve deformation and also stiffen the blade 20 as a result of the over pressure within the cavity 23.
    Type: Grant
    Filed: June 22, 2004
    Date of Patent: September 26, 2006
    Assignee: Rolls-Royce plc
    Inventors: Christopher M Whitehead, Simon Read
  • HIP manufacture of a hollow component
    Patent number: 7112301
    Abstract: Forming a hollow structure having an internal coating includes the steps of placing a core shaped to form the internal surface of the structure in a mould, filling the mould with a material powder, hot isostatically pressing the powder about the mould to consolidate the powder, and removing the core from the hollow structure formed, wherein a coating is applied to the core prior to placement in the mould, which coating bonds to the hollow structure formed, during the hot isostatic pressing, to form the internal coating.
    Type: Grant
    Filed: March 31, 2004
    Date of Patent: September 26, 2006
    Assignee: Rolls-Royce plc
    Inventors: George Thorne, Robert Charles Tonks, Wayne Eric Voice
  • Acceleration control in multi spool gas turbine engine
    Patent number: 7111464
    Abstract: A gas turbine engine system comprises a first compression stage; a second compression stage; a combustor; a controller; a first sensor for sensing the speed of the first compression stage and providing a first indication of the sensed speed to the controller; and a second sensor for sensing the speed of the second compression stage and providing a second indication of the sensed speed to the controller, wherein the controller is operable to control the supply of fuel to the combustor in dependence upon the first indication received from the first sensor and the second indication received from the second sensor. This arrangement is particularly useful in controlling the acceleration of an aero-engine from minimum idle.
    Type: Grant
    Filed: March 3, 2004
    Date of Patent: September 26, 2006
    Assignee: Rolls-Royce plc
    Inventor: Arthur L. Rowe
  • Pressure balanced annular seal
    Publication number: 20060208427
    Abstract: This invention provides a segmented annular seal (10) the sealing leakage gaps between relatively movable components 14,16 between high and low pressure regions in a gas turbine engine, for example for sealing an engine shaft 16. The seal comprises an annular array of circumferentially spaced and radially movable arcuate seal segments (12) which extend in a continuous end to end relationship in annular housing (14) and project radially from the housing for effecting a seal against an engine shaft (16), rotor or the like. The segments (12) are located in a channel (22) in the housing (14) sized such that the segments (12) are able to follow radial movements of the shaft (16). In order to reduce an axial loading on the segments (12) that ends to cause them to seize a pressure balance region (30) vented to the upstream pressure region is formed on the downstream side of the segments (12).
    Type: Application
    Filed: October 26, 2005
    Publication date: September 21, 2006
    Applicant: Rolls-Royce plc
    Inventors: Christopher Wright, Gervas Franceschini
  • Large radial movement compliant seal
    Publication number: 20060210392
    Abstract: A compliant seal provides a seal between an upstream region and a downstream region. The seal includes: a seal pack carrier defining a slot, the seal pack carrier having an upstream face and a downstream face; and a seal pack slideably mounted within the slot, the seal pack having an upstream face and a downstream face. The seal pack carrier and seal pack define a high-pressure plenum which abuts the downstream side of the seal pack, and which can be pressurised to apply a force to the seal pack in the upstream direction.
    Type: Application
    Filed: October 26, 2005
    Publication date: September 21, 2006
    Applicant: ROLLS-ROYCE PLC
    Inventor: Christian Enderby
  • Gas turbine engine blade containment system and a laminate material
    Publication number: 20060210391
    Abstract: A gas turbine engine blade containment system (22) comprising a laminate material (24). The laminate material (24) comprising first and second layers (26, 28). The second layer (28) comprising a plurality of deformable members (30) extending transversely relative to the first layer (26), each deformable member (30) being encased in a crushable support material (34). The deformable members (30) comprising springs (32). The first layer (26) being an inner layer within the second layer (28). The first layer (26) comprising a hard material to blunt a broken blade. The springs (32) in the second layer (28) are compressed and the crushable support material (34) of the second layer (28) is crushed to absorb energy of a broken blade.
    Type: Application
    Filed: October 27, 2005
    Publication date: September 21, 2006
    Applicant: Rolls-Royce plc
    Inventor: Alison McMillan
  • Production of disc components
    Patent number: 7107886
    Abstract: A disc component for a gas turbine engine is produced from a workpiece by a sequence of machining operations. During the machining operations, the workpiece is supported by a fixture engaging support surfaces. The workpiece remains secured to the fixture throughout the sequence of machining operations so that these operations can be conducted on both faces of a disc portion of the workpiece without removing the workpiece from the fixture. The machining operations are conducted alternately on the opposite faces in order to allow residual stresses in the workpiece to dissipate in a controlled manner.
    Type: Grant
    Filed: January 16, 2004
    Date of Patent: September 19, 2006
    Assignee: Rolls-Royce PLC
    Inventors: Christopher Peter Ralph Hill, Richard Church, Benjamin Mycock
  • Engine arrangement
    Patent number: 7107755
    Abstract: An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.
    Type: Grant
    Filed: July 31, 2002
    Date of Patent: September 19, 2006
    Assignee: Rolls-Royce plc
    Inventors: Karim El Hamel, Arnold C Newton
  • Turbofan arrangement
    Patent number: 7107756
    Abstract: A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The second propulsion system comprises a second fan shaft drivingly connecting to a second fan rotor and the first propulsion system and arranged so that the first and second shafts are not coaxial with one another.
    Type: Grant
    Filed: March 26, 2004
    Date of Patent: September 19, 2006
    Assignee: Rolls-Royce plc
    Inventor: Andrew M Rolt
  • Multi-shaft arrangement for a turbine engine
    Publication number: 20060201160
    Abstract: Elimination of a previous intermediate inter-shaft locating bearing allows smaller core sizes to be achieved and avoids relatively sophisticated design complications in order to provide that bearing. Thus, an inner shaft is supported at one end by a mounting bearing and at its other end by a spaced bearing combination upon a static cradle structure. The spaced bearing combination comprises bearings which can be varied in terms of spacing, stiffness of support upon the cradle and sprung resilience in the bearing races in order to tune shaft vibration to avoid critical frequencies occurring in the normal rotational running range of an engine incorporating the arrangement.
    Type: Application
    Filed: January 6, 2006
    Publication date: September 14, 2006
    Applicant: Rolls-Royce plc
    Inventor: Martyn Richards
  • Variable vane arrangement for a turbomachine
    Patent number: 7104754
    Abstract: A vane arrangement for a compressor of a gas turbine engine comprises a plurality of circumferentially arranged vanes, a plurality of levers and a control ring. Each vane comprises a fixed upstream portion secured to a casing and a movable downstream portion pivotally mounted to the casing. The movable portion of each vane is pivotally mounted at the upstream end of the movable portion adjacent the fixed portion of the respective vane. The movable portion of each vane has a spindle extending through an aperture in the casing. Each aperture in the casing has an elongate shape in cross-section and each aperture has a bush arranged within the aperture and around the spindle to fill the elongate shaped aperture. The downstream end of the fixed portion of each vane has substantially the same shape as the upstream end of the movable portion of the respective vane.
    Type: Grant
    Filed: May 13, 2004
    Date of Patent: September 12, 2006
    Assignee: Rolls-Royce plc
    Inventors: Matthew J Willshee, Dale E Evans
  • Sealing arrangement
    Patent number: 7101147
    Abstract: A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to each other in a flow path between a region of high fluid pressure and a region of low fluid pressure. The sealing arrangement comprises at least two resilient sealing strips, each strip having a portion formed along at least part of its width to locate in a groove provided along adjacent faces of the relatively moveable parts. The remaining portion of each of the sealing strips has a substantially flat surface which, in operation, abuts a corresponding flat surface of an adjacent sealing strip, thereby forming a seal.
    Type: Grant
    Filed: March 11, 2004
    Date of Patent: September 5, 2006
    Assignee: Rolls-Royce PLC
    Inventor: Julian G. Balsdon
  • Fluid vectoring nozzle
    Publication number: 20060186264
    Abstract: A fluid vectoring nozzle comprises flow vectoring means suitable for selectively producing a fluid dynamic throat in the nozzle in a plane oblique to the axis of the nozzle, such that in operation fluid flow passing through the throat is rotated about an axis parallel to and coincident with the plane of the throat. That is to say, the present invention comprises flow vectoring means suitable for selectively producing a fluid dynamic throat in the nozzle in a plane oblique to the axis of the nozzle, such that, in operation, fluid passing through the fluid dynamic throat is turned towards an angle perpendicular to the plane of the throat. Fluid injection means are provided to inject a control fluid into the nozzle through a perforate region provided in at least one nozzle wall, thereby generating a fluid dynamic restriction which initiates the formation of the fluid dynamic throat.
    Type: Application
    Filed: February 16, 2006
    Publication date: August 24, 2006
    Applicant: Rolls-Royce plc
    Inventor: Christopher Avenell
  • Turbine blade
    Publication number: 20060182633
    Abstract: A turbine blade 29 for a gas turbine engine 10 having an axis 20, the turbine blade 29 comprising: an aerofoil 30 including a high pressure surface 36, a low pressure surface 34, a root portion 38 and a tip surface 40 extending transverse from the high and low pressure surfaces 36 and 34, the high and low pressure surfaces 36 and 34 curve from the root portion 38 to the tip surface 40 in a direction that is substantially tangential to the axis 20 of the engine 10; and an air leakage restricting member 32 on the tip surface 40, the air leakage restricting member 32 being configured to substantially prevent leakage of air over the tip surface 40.
    Type: Application
    Filed: January 19, 2006
    Publication date: August 17, 2006
    Applicant: Rolls-Royce plc
    Inventor: Neil Harvey