Abstract: Described herein are nucleic acid detection compositions and systems comprising an internal nuclease chain reaction (NCR) for signal amplification and methods of using these NCR-containing compositions and systems.

Abstract: A machine such as a ship's engine has a superconducting component requiring cooling for its operation, and includes a cooling system. The cooling system is operable in first and second modes. In a cool-down phase the cooling system is run in the first mode providing relatively high heat transfer from the superconducting component. On attainment of a desired operating temperature the cooling system is run in the second mode, providing lower heat transfer. This enables a reduced cool-down time of the machine, while allowing economical operation in normal service. The higher level of cooling in the first mode used during the start-up procedure can involve a colder cryogen, or a greater flow of coolant. One way of achieving the latter is to circulate the coolant in normally evacuated regions during the cool-down phase, and then re-establishing the vacuum in these regions for normal service operation.

Abstract: A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between. The arrangement includes a heat transfer member extending from the first end at least part way along the body towards the second end. A heat source is arranged in use to heat the heat transfer member in the vicinity of the first end of the body. A plurality of thermal control layers are provided on the heat transfer member, each of the layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member. The arrangement may be used for prevention of icing of an aerofoil body such as a blade, vane or the like.

Abstract: A compressor is provided for pressurizing carbon dioxide produced by a carbon dioxide production plant and introducing the pressurized carbon dioxide to a carbon dioxide sequestration system. The compressor has a measuring system which determines the amount of carbon dioxide produced by the production plant. It also has a control system which varies the power of the compressor depending on the determined amount of produced carbon dioxide.

Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.

Abstract: A machine such as a ship's engine has a superconducting component 15 requiring cooling for its operation, and includes a cooling system 40. The cooling system is operable in first and second modes. In a cool-down phase the cooling system is run in the first mode providing relatively high heat transfer from the superconducting component. On attainment of a desired operating temperature the cooling system is run in the second mode, providing lower heat transfer. This enables a reduced cool-down time of the machine, while allowing economical operation in normal service. The higher level of cooling in the first mode used during the start-up procedure can involve a colder cryogen, or a greater flow of coolant. One way of achieving the latter is to circulate the coolant in normally evacuated regions 16 during the cool-down phase, and then re-establishing the vacuum in these regions for normal service operation.

Abstract: A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between. The arrangement includes a heat transfer member extending from the first end at least part way along the body towards the second end. A heat source is arranged in use to heat the heat transfer member in the vicinity of the first end of the body. A plurality of thermal control layers are provided on the heat transfer member, each of the layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member. The arrangement may be used for prevention of icing of an aerofoil body such as a blade, vane or the like.

Abstract: A compressor is provided for pressurising carbon dioxide produced by a carbon dioxide production plant and introducing the pressurised carbon dioxide to a carbon dioxide sequestration system. The compressor has a measuring system which determines the amount of carbon dioxide produced by the production plant. It also has a control system which varies the power of the compressor depending on the determined amount of produced carbon dioxide.

Abstract: A gas turbine engine arrangement (1) comprises a first gas turbine engine (10), a second gas turbine engine (70), a differential gearbox (57) and an electrical generator (112). The differential gearbox (57) has a first input drive (54), a second input drive (78) and an output drive (110). The output drive (110) of the differential gearbox (57) is arranged to drive the electrical generator (112) via an external, accessory, gearbox (56). The external, accessory, gearbox (56) drives other accessories (116, 120). The first gas turbine (10) is arranged to drive the first input drive (54) of the differential gearbox (57) and the second gas turbine engine (70) is arranged to drive the second input drive (78) of the differential gearbox (57). The electrical generator (112) and accessories (116, 120) are driven at a constant frequency speed/frequency.

Abstract: A drive arrangement for driving, or for being driven by, a fluid is disclosed. The drive arrangement comprises a rotatable member (40) for receiving the fluid, and having mounted thereon a plurality of drive members (56). The drive members (56) are movable between a drive position, in which the drive members can drive, or be driven by, the fluid, and a non-drive position in which the drive members (56) are substantially prevented from driving or being driven by a fluid received in the rotatable member (40).

Abstract: In order to achieve greater operational efficiency a propulsive arrangement is provided in which a relatively large number of small propulsive assemblies 9; 31, 32, 33 are provided in aircraft structures in particular the wing 7; 30. The assemblies 9; 31, 32, 33 comprise a flow path within which a compressor 39, 43, 47 is positioned to propel an air flow for propulsion. The compressors 39, 43, 47 are powered by electricity from an electricity generator 8 and possibly supplemented by solar cells or fuel cells or wing tip turbine generators 11. The assemblies 9, 31, 32, 33 are small to allow easy removal for maintenance and repair.

Abstract: A database arrangement is provided which presents a user with a results table 56. This had two dimensions. Column headings show classification headings at a selected level of a classification structure. The rows are classified with additional identification of the content of data items within the database. Each point of the table shows the number of data items meeting the two criteria. The user can thus see the number of results available from various alternative refinements of a search strategy, before the search strategy is restricted.

Abstract: An electrical power generation assembly comprising a main body having a low density to provide lift and wind driven means on its surface to generate electrical power. The main body has a part-circular, or a part-elliptical, cross section frontal region. The main body has a first distance and a second distance. The ratio of the first distance to the second distance is equal to or more than 0.5 and equal to or less than 5 according to the shape of the frontal region of the main body. The ratio of the diameter of the wind driven means to the first distance is equal to or less than 0.25.

Abstract: An indentor for contacting a bearing surface, the indentor comprising a contact surface complimentary to that of the bearing surface, wherein the indentor comprises an integral tapering portion which tapering portion defines part of the contact surface, the tapering portion at its distal edge defining an edge of contact between the contact surface and the bearing surface.

Abstract: A gas turbine engine fan blade (26) comprises a root portion (40) and an aerofoil portion (42). The aerofoil portion (42) has a leading edge (44), a trailing edge (46), a concave metal wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex metal wall portion (52) extending from the leading edge (44) to the trailing edge (46). The aerofoil portion (42) has a hollow interior (54) and the interior (54) of the aerofoil portion (42) is at least partially filled with a vibration damping material (56). The vibration damping material (56) comprises a material having viscoelasticity for example one formed by mixing an amine terminated polymer and bisphenol a-epichlorohydrin epoxy resin.

Abstract: A database arrangement is provided which presents a user with a results table 56. This had two dimensions. Column headings show classification headings at a selected level of a classification structure. The rows are classified with additional identification of the content of data items within the database. Each point of the table shows the number of data items meeting the two criteria. The user can thus see the number of results available from various alternative refinements of a search strategy, before the search strategy is restricted.

Abstract: An indentor for contacting a bearing surface, the indentor comprising a contact surface complimentary to that of the bearing surface, wherein the indentor comprises an integral tapering portion which tapering portion defines part of the contact surface, the tapering portion at its distal edge defining an edge of contact between the contact surface and the bearing surface.

Abstract: 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 (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.

Abstract: A gas turbine engine fan blade (26) comprises a root portion (40) and an aerofoil portion (42). The aerofoil portion (42) has a leading edge (44), a trailing edge (46), a concave metal wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex metal wall portion (52) extending from the leading edge (44) to the trailing edge (46). The aerofoil portion (42) has a hollow interior (54) and the interior (54) of the aerofoil portion (42) is at least partially filled with a vibration damping material (56). The vibration damping material (56) comprises a material having viscoelasticity for example one formed by mixing an amine terminated polymer and bisphenol a-epichlorohydrin epoxy resin.

Abstract: 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 assembly. The root member (42) includes bearing surfaces (46) for bearing against complementary surfaces (48) in the groove on rotation of the disc. The annulus filler (26) comprises a plurality of layers of carbon fiber reinforced plastics material, the layers being oriented substantially perpendicular to the bearing surfaces (46).