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| Number | Title | Issue Date |
| 6378293 | Gas turbine engine bearing arrangement A gas turbine engine (10) is provided with a plurality of shafts (18, 19, 20) interconnecting its compressor portions (11, 12, 13) with its turbine portions (15, 16, 17). Each shaft (18, 19, 20) is supported in the hotter part of the engine by electromagn... | 04/30/2002 |
| 6371721 | Gas turbine engine blade containment assembly A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally... | 04/16/2002 |
| 6360989 | Nacelle assembly for a gas turbine engine A nacelle assembly 40 adapted for mounting on a ducted fan gas turbine engine 20 comprising a generally annular body 46 having an air inlet 42 and an air outlet 44, the generally annular body 46 encircling a region of the engine 20 when working in operati... | 03/26/2002 |
| 6358013 | Turbine blade and manufacture thereof A gas turbine blade (10) which has a rounded trailing edge (18), is provided with a row of side by side arranged ceramic fibres (20) along the trailing edge (18). During operation of the turbine blade (10), the rounded shape of trailing edge (18) causes g... | 03/19/2002 |
| 6349537 | Vehicle main and auxiliary power units An aircraft gas turbine propulsion engine includes a compressor (10) and ancillary systems (cabin pressurizing pumps and other service) in a box 16. A fuel cell 18 powers electric motors (12) and (14) via a switch (20) for the purpose of either simultaneo... | 02/26/2002 |
| 6336472 | Pipe repair and replacement apparatus and method A pipe replacement apparatus includes a housing having upper and lower walls that are sealed together about a pipe section to be replaced; on the interior surfaces of the walls, tracks are provided for clamps with engage the original pipe and also carry t... | 01/08/2002 |
| 6336263 | Club and shaft separating device A shaft and club head separation device for a golf club includes a base having padded shaft gripping members and a separation disk having at least two peripheral recesses into which the end of shaft is inserted; the gripping members are arranged to mainta... | 01/08/2002 |
| 6334297 | Combuster arrangement A combustor arrangement (8) for a gas turbine engine (3) comprising a combustion chamber, fuel nozzles(52a,52b), and a bled diffuser (7) located upstream of said combustion chamber to, in use, direct an airflow from an upstream compressor (6) into the com... | 01/01/2002 |
| 6332313 | Combustion chamber with separate, valved air mixing passages for separate combustion zones A combustion chamber assembly (22) comprises a primary, a secondary and a tertiary fuel and air mixing ducts (54,78,98) to supply fuel and air to primary, secondary and tertiary combustion zones (40,42,44). Each of the primary, secondary and tertiary fuel... | 12/25/2001 |
| 6324828 | Gas turbine engine and a method of controlling a gas turbine engine A gas turbine engine comprises a centrifugal compressor (4), an air diffuser (8), a heat exchanger (10), combustion apparatus (12), and first and second turbines (14,18). The combustion chamber assembly (22) comprises a primary, a secondary and a tertiary... | 12/04/2001 |
| 6324830 | Gas turbine engines A fuel injector assembly designed to withstand a predetermined impact load resulting from ingestion of a bird or other foreign object into the combustion stage of a gas turbine engine comprises a body member adapted to be mounted adjacent to and to extend... | 12/04/2001 |
| 6312224 | Relating to bladed structures for fluid flow propulsion engines A component (24) for a gas turbine engine rotor assembly comprises a wall member (26) for at least partially bridging a space between adjacent rotor blades (18) and a root member (42) for insertion into a groove in the rotor disc (18) of the rotor assembl... | 11/06/2001 |
| 6299986 | Coated superalloy article and a method of coating a superalloy article A high rhenium-containing nickel superalloy article (10) has a multilayer coating (12) comprising a barrier coating (14) and an aluminide coating (16). The aluminide coating (16) is a corrosion and oxidation protective coating for the superalloy article (... | 10/09/2001 |
| 6293086 | Power generation equipment Power generation equipment (10) comprises a compressor (11,12) into which finely dispersed water is directed. Air compressed by the compressor (11,12) is directed into combustion equipment (13) where it is mixed with steam and fuel before combustion takes... | 09/25/2001 |
| 6289667 | Combustion chamber and a method of operation thereof A catalytic combustion chamber is provided with at least two cataleptic combustion zones arranged in flow series, In a first mode of operation fuel is supplied from first fuel injectors, positioned upstream of the first catalytic combustion zone, into the... | 09/18/2001 |
| 6286361 | Method and apparatus for remotely detecting pressure, force, temperature, density, vibration, viscosity and speed of sound in a fluid An apparatus for detecting pressure in a hollow fan blade of a turbofan gas turbine engine comprises a magnetostriction transducer arranged in a sub chamber of the fan blade which is interconnected to a main chamber. A magnetic coil is arranged in the fan... | 09/11/2001 |
| 6283707 | Aerofoil blade damper An aerofoil blade damper comprising an elongate member which is inserted within a core passage of the blade and extends within the blade with the damper retained therein at one end which is closest to the blade root with the remainder of the damper free t... | 09/04/2001 |
| 6283713 | Bladed ducting for turbomachinery An axial flow turbomachine has at least one circumferential row of aerofoil members in which at least one of the two end walls (33) between successive blades (30) is given a non-axisymmetric profile to modify the boundary layer flow at the wall. In one fo... | 09/04/2001 |
| 6273135 | Fuel flow control apparatus A high pressure fuel system includes tapped high pressure flows (22,24) with restrictors (44,46) to provide low pressure flows with which, via a valve (50) to enable either a low pressure flow to bias a main, high pressure fuel cut off valve (16) to close... | 08/14/2001 |
| 6273824 | Flexible diaphragm shaft coupling assembly A flexible coupling between drive and driven shaft members includes a diaphragm member having an offset base and outer periphery that is relatively more flexible than the radially inner base which is formed integrally with one of the shaft members or at l... | 08/14/2001 |
| 6267557 | Aerofoil blade damper A damping member (27) for positioning between the undersides of the platforms of adjacent turbine blades (20) and the peripheral surface of a disc (19) upon which the turbine blades (20) are mounted. The damping member (27) comprises first, second and thi... | 07/31/2001 |
| 6267381 | Resilient strip seal arrangement A seal for effecting a seal between two components (2,4) to inhibit a flow of fluid, between the two components, in a sealing direction (22) from an upstream side (24) of the seal to a downstream side (26) of the seal. The downstream side (26) of the seal... | 07/31/2001 |
| 6264428 | Cooled aerofoil for a gas turbine engine A hollow cooled aerofoil blade (10) is provided with a central, lengthways extending plenum (16) and has pressure and suction flanks (20,15). The suction flank (15) has lengthways extending passages (21) therein that direct cooling air from the root regio... | 07/24/2001 |
| 6264091 | Method of manufacturing an article by diffusion bonding A method of diffusion bonding at least two metal workpieces (12, 14, 16) comprises assembling the workpieces (12, 14, 16) into a stack (10) relative to each other so that the surfaces (18, 20, 22, 24) are in mating contact. The edges of the workpieces (12... | 07/24/2001 |
| 6254344 | Seal An annular seal comprising a mass of bristles (10) packed together in a layer axially adjacent to an annular backing plate (12). The bristles (12) and backing plate (14) are mounted on and extend from a radially outer member (4) towards and around a cylin... | 07/03/2001 |
| 6253555 | Combustion chamber comprising mixing ducts with fuel injectors varying in number and cross-sectional area A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fu... | 07/03/2001 |
| 6251341 | Method for treatment of fluent products An apparatus and method for the heat treatment of a fluent food product with steam includes a pressure vessel having a steam inlet at one end and an a product outlet at the opposite end; an inner partition wall having an open end defines the product intro... | 06/26/2001 |
| 6240732 | Fluid manifold A fluid manifold (41) comprises two annular chambers (42 and 46) in flow series and having a barrier (45) therebetween. A fluid is fed into the first larger annular chamber (42) and circulates circumferential therethrough before being passed through a plu... | 06/05/2001 |
| 6241468 | Coolant passages for gas turbine components A gas turbine engine component, typically either a turbine blade or vane or combustor, comprising a wall (40) with a first surface (39) which is adapted to be supplied with a flow of cooling air, and a second surface (38) which is adapted to be exposed to... | 06/05/2001 |
| 6237343 | Combustion chamber and a method of operation thereof A gas turbine engine (10) combustion chamber (28) comprises a primary combustion zone (36) and a secondary combustion zone(40) in which lean mixtures of fuel and air are burned. Air is supplied to a first mixing duct (50) through a swirler (52). Air is su... | 05/29/2001 |
| 6220423 | Lumber feed system with load responsive speed modulation The disclosure describes a system to provide a steady supply of lumber pieces to a board separating device and insure the correct positioning of each lumber piece, at the proper time, thus allowing the separating device to function at a substantially high... | 04/24/2001 |
| 6220602 | Seal arrangement A seal arrangement (40) between relatively movable components (42,48) includes at least one magnet (54) on a first component (48) and at least one magnet (56) on the second component (42). A clearance (55) is defined between the at least one magnet (54) o... | 04/24/2001 |
| 6219404 | Method of determining if an alloy article has any remaining working life A method of determining if an alloy article (28) has any remaining working life comprises taking a sample from an alloy article (28) and removing all metal matrix material from the sample to leave the carbide particles. The carbide particles are analysed ... | 04/17/2001 |
| 6216981 | Environmental control system An environmental control system which is particularly suitable for use in aircraft comprises an air compressor (22) and an expansion turbine (36). The air compressor (22) is electrically driven at its optimum speed to deliver compressed air to the turbine... | 04/17/2001 |
| 6205771 | Ducted fan gas turbine engine control system A control system for a ducted fan gas turbine engine (10) comprises a control unit (29) that receives input signals from a pressure transducer (27) located within the engine's fan duct (11) downstream of the fan (13) and a rotational speed transducer (32)... | 03/27/2001 |
| 6193247 | Portable stackable wagon assembly A portable, stackable wagon assembly includes a main compartment over which a handle structure is movable to an operational position; the main compartment includes side walls provided with support members for a tray that is insertable into the main compar... | 02/27/2001 |
| 6189814 | Gas turbine engine combustion chamber A gas turbine combustion chamber which has primary, secondary and tertiary combustion zones in flow series has a secondary mixing duct and a tertiary mixing duct. The secondary and tertiary mixing ducts reduce in cross-sectional area from their intakes to... | 02/20/2001 |
| 6183375 | Apparatus and method for tuning a golf shaft A method of making a golf club includes making a first determination of the location of the effective seam in a shaft and then more precisely locating the seam before attaching a golf club head with the face of the club head facing in a neutral direction.... | 02/06/2001 |
| 6179557 | Turbine cooling Shrouds (40) surrounding a stage of turbine blades (44) are cooled by a compressor airflow which is led to the downstream end of the shrouds before contacting them. The airflow passes through apertures (56) in plates (50) then over the shrouds (40) in an ... | 01/30/2001 |
| 6179551 | Gas turbine containment casing A containment casing for a gas turbine engine comprising a substantially rigid casing shell arranged in operation coaxially with an axis of rotation of the gas turbine engine. The casing extending circumferentially around an array of fan rotor blades whic... | 01/30/2001 |
