| Patent Number |
Title Of Patent |
Date Issued |
| RE35664 |
Friction welding |
November 18, 1997 |
| The present invention consists in the apparatus for use in welding a first component and a second component together by friction welding, comprising drive means operative to generate reciprocatory movement, a component holder operative to hold said first component, linking means operativ |
| RE34398 |
Apparatus for and method of manufacturing brush seals |
October 5, 1993 |
| This invention provides an apparatus for and method of manufacturing a brush seal. The apparatus comprises an annular former 22 having a radially outer 24 and a radially inner 30 portion radially separated from each other by an amount G and held relative to each other by locating means 3 |
| RE34235 |
Sealing plug |
April 27, 1993 |
| A sealing plug .Iadd.assembly .Iaddend.includes a plug and a housing.Iadd., .Iaddend.the plug and the housing including co-operating .[.means.]. .Iadd.structures .Iaddend.whereby they may be secured together, the plug including two circumferentially extending grooves within which O ring |
| 7451592 |
Counter-rotating turbine engine including a gearbox |
November 18, 2008 |
| A turbine engine arrangement is provided in which contra rotating shafts 104, 105 are respectively secured to a fan and a gearbox 106 which is also coupled to the shaft 104. In such circumstances the relative rotational speed ratio between the shafts 104, 105 can be determined with a |
| 7449063 |
Method and mould for casting articles with a pre-determined crystalline orientation |
November 11, 2008 |
| Previously a number of techniques have been used in order to form single crystal or pre-determined crystallography components and articles. Each one of these techniques has its own particular problems, including susceptibility to error. By utilisation of a bi-crystal experiment to de |
| 7448851 |
Seal arrangement |
November 11, 2008 |
| A seal arrangement 30 presents a barrier in the form of a combined seal and anti-fret liner 36 across a shroud ring cavity 32 in order to inhibit air leakage in the platform gap between platforms 33. It will be understood that these gaps are provided for thermal expansion and vibrati |
| 7448849 |
Seal |
November 11, 2008 |
| A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) |
| 7448845 |
Gas turbine engine |
November 11, 2008 |
| A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a plurality of circumferentially spaced radially outwardly |
| 7448215 |
Combustion chamber for a gas turbine engine |
November 11, 2008 |
| A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extending through its wall f |
| 7445685 |
Article having a vibration damping coating and a method of applying a vibration damping coating |
November 4, 2008 |
| A compressor blade (30) comprises a vibration damping coating (54) on a first surface of at least one portion of an erosion resistant material (56). The vibration damping coating (54) comprises a plurality of segments (58). The portion of erosion resistant material (56) and the vibra |
| 7445433 |
Fan or compressor blisk |
November 4, 2008 |
| A fan or compressor blisk for a gas turbine engine, lift fan or the like, comprises a disc having a radially outer rim, and a plurality of aerofoil blades circumferentially spaced around and extending radially outwards from the rim. The rim has a radially inward facing surface on its |
| 7445425 |
Seal assembly |
November 4, 2008 |
| A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided between the segments 38,40. A strip 46 is cemented into the slot |
| 7445421 |
Fan duct blade containment assembly |
November 4, 2008 |
| The fan cowl (12) of a ducted fan gas turbine engine (10) has a downstream portion including an inner casing (30) that surrounds a honeycomb structure (36) in abutting engagement. Honeycomb structure (36) is made up of a number of closely spaced honeycomb blocks (36a) fixed about a l |
| 7444826 |
Fault current limiter |
November 4, 2008 |
| A fault current limiter comprising: an input node; an output node; a variable impedance element coupled between the input node and the output node; a multi-cycle refrigeration system, comprising a first coolant cycle for cooling the variable impedance element and a second coolant cyc |
| 7444802 |
Gas turbine engine including stator vanes having variable camber and stagger configurations at d |
November 4, 2008 |
| Within an intake for a gas turbine engine provision is provided through stator vanes 25, 45 in the stator whereby back pressure from a necessary obstruction 34, 46 can be utilised to balance forward pressure variations caused by intake droop or crosswinds in order to reduce those forward |
| 7442008 |
Cooled gas turbine aerofoil |
October 28, 2008 |
| An internal fluid cooling system for a gas turbine aerofoil comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage in the interior of the aerofoil. The cooling fluid--in particular air--is supplied to an inlet end of each passage and exhau |
| 7438528 |
Component having a cooling arrangement |
October 21, 2008 |
| A component such as a turbine blade for a gas turbine engine has a cooling arrangement comprising a supply passage 18 within the blade from which extend cooling passages 28 of a first array which open at discharge openings 29, for example at a trailing edge of the blade. Cooling pass |
| 7438526 |
Large radial movement compliant seal |
October 21, 2008 |
| 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 |
| 7438518 |
Gas turbine nozzle guide vane |
October 21, 2008 |
| A nozzle guide vane for a gas turbine comprises at least one aerofoil having a leading edge section provided with at least one internal cavity for conveying cooling fluid through the said leading edge section, and a plate like wall section extending from the leading edge section to p |
| 7438262 |
Redundant gas turbine engine mounting arrangement |
October 21, 2008 |
| A gas turbine engine mounting arrangement for attaching a gas turbine engine to a support structure, such as a pylon of an aircraft, comprises a main mounting member adapted to interconnect the engine with the pylon and transmit loads therebetween under normal engine operating conditions |
| 7435290 |
Centrifugal gas/liquid separators |
October 14, 2008 |
| A centrifugal gas/liquid separator for location in a liquid reservoir comprises a generally cylindrical wall defining a separation chamber having a closed end, an open end, an inlet in the cylindrical wall for supplying a gas/liquid mixture into the separation chamber, and a gas outl |
| 7431564 |
Turbine blisk |
October 7, 2008 |
| A blisk for use in the turbine section of a gas turbine engine comprises a disk around the circumference of which is disposed a plurality of blades in an annular array. The blades are preferably cast separately and then joined, for example by welding, so that the roots form a continuous |
| 7430867 |
Gas turbine multiple sectioned exhaust duct |
October 7, 2008 |
| A duct comprising an inner casing spaced apart from an outer casing and which also comprises a number of interfaced duct sections must be assembled in such a way to prevent relative redial movement between the casings and thereby inhibit buckling. The present invention is a duct whic |
| 7428475 |
Method of processing oscillatory data |
September 23, 2008 |
| A method which permits the transformation of non-stationary response measurements into stationary data for analysis is provided. Many standard analysis techniques, particularly for oscillatory responses, are based on stationary data, and the method allows these techniques to be performed |
| 7422820 |
Solid oxide fuel cell stack |
September 9, 2008 |
| A solid oxide fuel cell stack (10) comprises a plurality of modules (12). Each module (12) comprises an elongate hollow member (14). Each hollow member (14) has at least one passage (32) extending longitudinally through the hollow member (14) for the flow of reactant. Each hollow mem |
| 7419082 |
Friction welding process |
September 2, 2008 |
| A friction welding process providing a workpiece having a weld surface, and a second workpiece having a weld surface. The workpieces being welded together at respective weld surfaces. Oscillatory motion is affected to the workpieces such that one weld surface moves across the other, ther |
| 7418821 |
Aircraft gas turbine engines |
September 2, 2008 |
| An aircraft gas turbine engine including a first hydraulic pump connected to a starter motor and a second hydraulic pump connected to the high-pressure compressor. The engine being arranged such that during starting the starter motor drives the first pump, to pump hydraulic fluid to |
| 7413194 |
Pressure balanced annular seal |
August 19, 2008 |
| 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 |
| 7410705 |
Rare earth-transition metal alloy articles |
August 12, 2008 |
| A phosphate bonded ceramic is used to provide a protective coating on a rare earth-transition metal (RE-TM) alloy substrate, conferring degradation resistance to the alloy by being oxidation resistant and acting as a diffusion barrier, thereby minimising/preventing oxygen diffusion a |
| 7410089 |
Method of making aerofoil blisks |
August 12, 2008 |
| A method of making an aerofoil blisk (10) comprising a plurality of aerofoil blades (12) joined to a disc (14) to extend radially outwardly therefrom includes the step of forming a blade member (28) having a stub (30) for joining to the disc (14), the stub (30) having a taper ratio of |
| 7409855 |
Engine health monitoring |
August 12, 2008 |
| The present invention is a method of monitoring the health of a fuel system 30 of a gas turbine engine 10. The fuel system 30 comprising a fuel-metering valve 36, a hydraulic control valve servo pressure line 40 and a control pressure line 39. The fuel-metering valve comprises a hydr |
| 7409848 |
Apparatus and method for bulge testing an article |
August 12, 2008 |
| An apparatus (10) for bulge testing an article (12) comprises a pressure vessel (14) arranged to define a chamber (15), the pressure vessel (14) has a first aperture (28) and a second aperture (30), means to pressurize the chamber (15), means (19) to measure the deflection of the article |
| 7407622 |
Method of manufacturing a metal article by powder metallurgy |
August 5, 2008 |
| A method of manufacturing a fan blade (26) for a gas turbine engine by powder metallurgy comprises the steps of forming a container (52) and placing at least one metal insert (52) at a predetermined position within the container (52) and filling the container (52) with metal powder (60). |
| 7407365 |
Cooling arrangement |
August 5, 2008 |
| The present invention relates to a cooling arrangement in which a fractal passage network is provided incorporating several passage stages. Each passage stage 4, 5, 6, 7 has substantially the same passage cross-section for consistency with other passage stages to facilitate flow pressure |
| 7404925 |
Method of analysing a temperature indicating paints using a marker paint |
July 29, 2008 |
| A marker paint comprises 42 wt % to 52 wt % pigment, 31 wt % to 37 wt % acrylic resin and 17 wt % to 21 wt % silicone resin excluding solvent. The pigment comprises cobalt titanium oxide, titanium nickel antimony oxide, cobalt aluminium oxide or cadmium sulphide selenium to give a gr |
| 7402022 |
Rotor blade containment assembly for a gas turbine engine |
July 22, 2008 |
| A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, casing (40). The casing (40) having at least one member (54) and the member (54) has a first portion (53) extending radially from the casing (40) and a second portion (55) |
| 7400994 |
Method and test component for rotatable disc parts |
July 15, 2008 |
| Rotatable discs combined with turbine blades in engines must be tested for critical life analysis. Thus, consideration must be made as to life expectancy for such components as a result of tensile circumferential hoops as generated by the weight of blades under rotation as well as co |
| 7400286 |
Device and method for use in the verification of handwriting |
July 15, 2008 |
| A device (10) for use in the verification of handwriting, comprising: a body (12) having a surface (11) over which a writing instrument (8) is moved during the generation of a piece of handwriting; a transducer (14) for transducing stress-wave activity in the body (12) to an analogue tim |
| 7399546 |
Solid oxide fuel cell |
July 15, 2008 |
| A solid oxide fuel cell (10) comprises an anode electrode (12), a cathode electrode (14) and an electrolyte (16) between the anode electrode (12) and the cathode electrode (14). A gaseous fuel is supplied to an anode chamber (18) partially defined by the anode electrode (12) and a gaseou |
| 7399160 |
Turbine component |
July 15, 2008 |
| A turbine component such as a turbine blade has a cooling chamber that is tapered. The taper induces and maintains a helical swirl that improves the cooling efficiency of the cooling process and enables the turbine component to operate at higher temperatures. |
| 7399158 |
Blade arrangement |
July 15, 2008 |
| A blade arrangement 31 includes an array of radially extending blades 20, which may for example comprise a fan of a gas turbine engine for an aircraft. The blades 20 are mounted for rotation about a central axis X-X. The blade arrangement 31 further includes a damping arrangement 32 |
| 7398641 |
Aeroengine intake having a heat exchanger within an annular closed chamber |
July 15, 2008 |
| A gas turbine engine comprising a nacelle having an intake, the intake defining a generally annular chamber, an engine accessory and a heat exchanger for cooling a fluid of the accessory. The chamber is closed and the heat exchanger is disposed within the chamber operable to provide |
| 7396203 |
Spacer arrangement |
July 8, 2008 |
| A spacer arrangement 1, 40 is provided in which wedges 5, 6; 45, 46 are arranged to have an interface 7, 47 between them such that a thermally variable member 8, 48 can cause relative motion between the wedges 5, 6; 45, 46 to adjust an arrangement lateral dimension dependent upon tem |
| 7395669 |
Gas turbine engine combustor |
July 8, 2008 |
| A combustor for a gas turbine engine comprising at least one combustor air intake chute wherein at least one of the air intake chutes is configured to enhance the heat transfer relationship between the chute material and the air flowing over it. The air intake chutes have at least one ra |
| 7388680 |
Gap monitor arrangement |
June 17, 2008 |
| Monitoring of clearance gaps between a rotating component and a surrounding cowling surface is difficult in view of the general packaging constraints. Furthermore, when such operation occurs at high temperature there may be distortion in view of natural expansion and contraction over |
| 7387445 |
Bearing housing |
June 17, 2008 |
| A bearing housing 1 is designed to accommodate a bearing 4 within its outer walls 3. The bearing 4 upon rotation generates a centrifugally dispersed oil spray from its peripheral edge 7 and this spray is collected upon a facing surface of the wall 3. An out-take 6 has a relatively wi |
| 7384439 |
Vents for fluid systems |
June 10, 2008 |
| A vent for a fluid system includes a chamber through which fluid can flow along either a first flow path or a second flow path, in which the resistance to fluid flow is relatively high when the fluid follows the first flow path and relatively low when the fluid follows the second flow |
| 7384240 |
Composite blade |
June 10, 2008 |
| A composite blade (26) comprises a root portion (36) and an aerofoil portion (38). The aerofoil portion (38) has a tip (42), a chord (C), a leading edge (44), a trailing edge (46), a suction surface (48) extending from the leading edge (44) to the trailing edge (46) and a pressure su |
| 7381477 |
Rare earth-transition metal alloy articles |
June 3, 2008 |
| This invention provides a rare earth-transition metal (RE-TM) alloy structure comprising a RE-TM alloy substrate and a noble metal diffusion barrier disposed thereon. The noble metal diffusion barrier may be provided on the surface of the alloy substrate by an electroplating techniqu |
| 7378845 |
NMR methods for measuring fluid flow rates |
May 27, 2008 |
| A method for measuring fluid flow rates comprises the steps of: (a) creating a non-oscillating magnetic field of a predetermined strength across a flowing fluid; (b) performing the sub-steps of: (i) exposing the flowing fluid to an oscillating magnetic field pulse orthogonal to the n |
