Quotables
"Without question, the greatest invention in the history of mankind is beer. Oh, I grant you that the wheel was also a fine invention, but the wheel does not go nearly as well with pizza."
Dave Barry
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 7164220 | Stator pole structure for an electrical machine An electrical machine, such as a transverse flux motor, incorporates a stator core assembly 1. The stator core assembly 1 comprises a stator frame 4 upon which stator cores 2,3 are located with spacer elements 7 therebetween. A num... | 01/16/2007 |
| 7163086 | Lubrication system A lubrication system comprises a reservoir for lubricant, lubricant delivery means to deliver lubricant to at least one component to be lubricated, an injector associated with each component, a control system to control the opening and closing of each injector and s... | 01/16/2007 |
| 7162875 | Method and system for controlling fuel supply in a combustion turbine engine In order to regulate fuel flow to the combustor (36) of the combustion turbine engine (10) having a primary combustion zone (64) and at least one further combustion zone, the temperature of the inlet and outlet of the combustor (36) are d... | 01/16/2007 |
| 7164123 | Method for filtering spurious resonances from an NMR dataset A method for filtering spurious resonances from an NMR dataset comprises the steps of: (a) creating a first, non-oscillating magnetic field of a predetermined field strength across a sample, (b) intermittently expo... | 01/16/2007 |
| 7161486 | Electrostatic sensors A sensor 10 comprises an array of electrostatic sensor elements 12, each centred at a respective sensing position 14. Each element produces a respective output signal at 16. The outputs 16 can be used to drive respective pixels of ... | 01/09/2007 |
| 7160066 | Mounting arrangement and method A mounting arrangement 1 is provided in which clamping pairs comprising a clamping pad 2 and seating pads 3 are arranged about a mounting end of a component 4. Thus, the component 4 is appropriately presented to a machining device ... | 01/09/2007 |
| 7159872 | Seal arrangement A seal arrangement (73) is provided in which seal elements (77) incorporate passages (90) allowing an air flow to be presented to tip edges (78) of the seal elements, in order to create air suspension and diminish excessive wear. These pa... | 01/09/2007 |
| 7160159 | Drive apparatus A drive apparatus (10) for propelling a vehicle across a body of water is described. The apparatus (10) comprises a prime mover, for example a gas turbine engine (12), and a propelling arrangement (26) driven by the prime mover for propel... | 01/09/2007 |
| 7158919 | Remote monitoring system A remote monitoring system including a sub-system, local to a nuclear power plant and a remote sub-system at an operations base. Process data is collected manually by a hand-held computer and automatically by instrumentation on the power plant. The data collected is... | 01/02/2007 |
| 7153091 | Gas turbine engine 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 pluralit... | 12/26/2006 |
| 7153103 | Fan blade and disk assembly A gas turbine engine fan blade (22) and disk assembly (30) is provided with levers (36) with which to apply a force to the radially inner end of respective blades (22) so as to move the roots (26) of the blades (22) into abu... | 12/26/2006 |
| 7147431 | Cooled turbine assembly A gas turbine engine (10) is provided with a stage of turbine blades (22) surrounded by hollow shroud segments (28). Cooling of the shroud segments (28) is achieved by providing a flow of engine leakage air from space volume (48) c... | 12/12/2006 |
| 7143975 | Landing arrangement for an aircraft A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22 | 12/05/2006 |
| 7146291 | Method of generating an inspection program and method of generating a visual display A computer-implemented method of generating an inspection program for a computer-controlled coordinate measuring probe comprises the steps of: (a) receiving nominal geometry data for a component, (b) receiving insp... | 12/05/2006 |
| 7137781 | Turbine components A turbine component, such as a turbine blade 1, 21, has a coolant supply passage 4, 24 and a cooling chamber 3, 23 connected by an injection passage 5, 25. The cooling chamber 3, 23 includes flow guides in the form of vanes 7, 8... | 11/21/2006 |
| 7137282 | Laser shock peening In a laser shock peening process, the shape of the spot generated by the laser beam is changed on the fly. This is achieved, for example, by a masking device which is movable into and out of the path of the laser beam. Laser shock peening spots can consequently be s... | 11/21/2006 |
| 7135867 | Method and apparatus for verifying connectivity of an instrumentation system An instrumentation system including a plurality of sensors attached to a test piece, each of the sensors provided with an electrical signal generating device and an electrical signal measurement device. Each sensor is located remotely from its electrical signal meas... | 11/14/2006 |
| 7134269 | Gas turbine engine A gas turbine engine (10) comprises a second compressor (14), a first compressor (16), a heat exchanger (18), a combustor (20), a first turbine (22), a second turbine (24) and a third turbine (26) arranged in f... | 11/14/2006 |
| 7134344 | Control method and apparatus An adaptive control method is provided with particular relevance in methods which use a varying input frequency for analysis of an oscillatory response of a system, such as sine sweep testing. In one aspect the method includes the steps of applying a drive force hav... | 11/14/2006 |
| 7132606 | Stator coil assembly A stator coil assembly comprising a stator coil and a mounting platform for the stator coil. The coil has an earth wrap and is bonded to the mounting platform by a resiliently deformable bonding layer. The bonding layer is an electrical insulator formed from silicon... | 11/07/2006 |
| 7125010 | Work piece holding arrangement A work piece holding arrangement (10) includes an array of engagement elements (12) for engaging a work piece. The arrangement (10) also includes an actuator (34) for moving a plurality of the engagement elements (12) into engageme... | 10/24/2006 |
| 7124856 | Acoustic liner for gas turbine engine A passive acoustic liner system (50) for attenuating a sound field comprising, in acoustic series, a mode-scattering segment (48) and a sound-absorbing segment (40), wherein the mode scattering segment (48) provides a reactance between âˆ... | 10/24/2006 |
| 7125217 | Cellular materials A structural member comprises a main body formed from a cellular material. The structural member may be a casing for a rotary assembly e.g. a fan of a gas turbine engine. The main body may incorporate strengthening ribs and conduits and may have a random or graduate... | 10/24/2006 |
| 7121789 | Arrangement for mounting a non-rotating component An arrangement 22 for mounting a non-rotating component 28 of a gas turbine engine 10, defining a portion of a gas path of the gas turbine engine 10 comprising: a non-rotating component 28 having an opening 23 to a receptacl... | 10/17/2006 |
| 7121758 | Joint arrangement A joint assembly 80 is provided for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising. In its simplest form, the joint 80 comprises a first member 40 having a portion 82 and a s... | 10/17/2006 |
| 7118346 | Compressor blade A compressor blade (26) comprises an aerofoil (36) and a root (38). The aerofoil (36) comprises a concave wall (40) extending from a leading edge (44) to a trailing edge (46) and a convex wall (42) extending fr... | 10/10/2006 |
| 7117679 | Fuel injection In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements inclu... | 10/10/2006 |
| 7118818 | Solid oxide fuel cell system A system comprising a solid oxide fuel cell stack and a gas turbine engine. The stack comprises a plurality of solid oxide fuel cells, each fuel cell comprises an electrolyte, an anode and a cathode. The gas turbine engine comprises a compressor and a turbine with t... | 10/10/2006 |
| 7118331 | Stator vane assembly for a turbomachine A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes (32), the axial position of the stator vanes (32) and/or the pitch angle circumferentially between adjacent stator vanes (32) is varied c... | 10/10/2006 |
| 7114917 | Vane assembly for a gas turbine engine 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 stru... | 10/03/2006 |
| 7112301 | HIP manufacture of a hollow component 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... | 09/26/2006 |
| 7112044 | Blades 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 ... | 09/26/2006 |
| 7111464 | Acceleration control in multi spool gas turbine engine 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 ... | 09/26/2006 |
| 7107756 | Turbofan arrangement 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 fir... | 09/19/2006 |
| 7107755 | Engine arrangement 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 fro... | 09/19/2006 |
| 7104754 | Variable vane arrangement for a turbomachine 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 pivotal... | 09/12/2006 |
| 7090165 | Aeroengine nacelle A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and compris... | 08/15/2006 |
| 7092845 | Computational design methods A method of identifying a configuration of an object, the method comprising the steps of: specifying a plurality of different object configurations; for each specified object configuration, using a first simulation procedure to simulate the specified conditions so a... | 08/15/2006 |
| 7090463 | Guide vane A guide vane 100 is provided in which sheet portions 14, 15 are secured together to define an aerofoil profile 11. Between ends 20, 21 of the guide vane 100 there is a non linear variation in the maximum chordal thickness 13... | 08/15/2006 |
| 7089742 | Wall elements for gas turbine engine combustors A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality... | 08/15/2006 |
