Abstract: A lumber processor includes slowdown conveyor to transition lumber pieces from one processing device to a subsequent processing device where the movement of lumber pieces changes from lineal to lateral motion; a printer station includes a printer boom which includes a lateral translation device to move a symbol printer over the path of travel of the conveyor to allow the printer to mark pieces of lumber that are passing beneath the printer station.

Abstract: A seal segment (66) as described for a seal segment ring (64) of a turbine (16) in a gas turbine engine (10). The seal segment (66) has an inner surface (70) adapted to face the turbine blades (36) in use. Path means (72) is defined in the seal segment (66). The path means (72) is adapted to extend, in use, generally parallel to the principal axis of the turbine and has downstream inlet means (74) through which a cooling fluid to cool the seal segment can enter the path means (72) and upstream outlet means (76) from which the cooling fluid can be exhausted from the path means (72). The cooling fluid can flow along the path means (72) in a generally upstream direction opposite to the flow of gas through the turbine.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.

Abstract: A method of manufacturing a gas turbine engine fan blade (10) comprises forming three metal workpieces (50,52,54). A metal slab (30) is upset forged at both ends (32,34) to produce a metal block (40) with increased thickness (42,44) extending from opposite surfaces (36,38). The metal block (40) is cut in an inclined path to form two of the metal workpieces (50,52). The metal workpieces (50,52,54) are assembled into a stack (56) so that the flat surfaces (38,42,46,48) are in mating abutment. Heat and pressure is applied across the thickness of the metal workpieces (50,52,54) to diffusion bond the metal workpieces (53,52,54) together to form an integral structure (100). The integral structure (100) is hot creep formed and superplastically formed to produce the required aerofoil shape and the thickened end is machined to form the blade root (26). The method enables thinner metallic workpieces with better microstructure to be used and increases the yield of metallic workpieces.

Abstract: 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 fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).

Abstract: A device (10) for fatigue testing of materials comprises a frame (14), first and second clamping means (16,18) for holding a specimen (12) to be tested. First and second mounting means (20,22) mount the clamping means (16,18) on the frame (14). The mounting means (20,22) vibrationally isolate the clamping means (16,18) from the frame (14). Actuator means (24) moves the first clamping means (16) relative to the second clamping means (18) to apply a low cycle load on the specimen (12). Electrical insulating means (30) electrically insulate the frame (14) from the specimen (12). A shaker (26) is coupled to the second clamping means (18) to apply a high cycle load on the specimen (12). A detector (32) detects the vibration of the specimen (12) and sends an electrical signal to a control unit (42) which determines the resonant frequency of the specimen (12). The control unit (42) sends a signal to the shaker (26) to maintain the high cycle load at the resonant frequency of the specimen (12).

Abstract: An electrical machine, such as a generator or motor, is incorporated in a gas turbine engine. The engine has compressor blades which are shrouded at. Beyond the shroud, an electrical machine is provided by rotor projections which run in a channel in flux cores, with which excitor coils are associated. The result is an electrical machine which is external to the combustion gas paths of the engine, for ready access, and can have optimized magnetic flux paths for efficiency. High relative speeds within the electrical machine provide further advantages.

Abstract: A wind energy converter includes a support arm or post rotatably mounted on a base and having an upper free end; a pivot arm is pivotally mounted on the free end and has an end remote from the support arm; a pair of vanes are mounted on a pivot rod carried at the end of the pivot arm so that the vanes are free to rotate about the pivot rod; abutment arms are provided on the end of the pivot arm to limit the arc through which the vanes may rotate; at the other end of the pivot arm a linkage structure is provided to connect the other end of the pivot arm to an electrical generator.

Abstract: A thrust reverser cascade flow directing element (28) for a gas turbine engine (10) comprises a plurality of plates (30) and a plurality of flow directing vanes (40). At least one vane (40) extends between each pair of plates (30), the plurality of plates (30) are formed from sheet material and a single integral piece of ductile sheet material (32) forms the plurality of flow directing vanes (40). The single integral piece of ductile sheet material (32) has a plurality of longitudinally spaced apart apertures (36) and a plurality of longitudinally spaced apart sheet material portions (38) between the apertures (36) and the ductile sheet material (32) is bent at a plurality of longitudinally spaced positions such that each sheet material portion (38) defines one of the plurality of flow directing vanes (40).

Abstract: A black high temperature emissivity paint comprises 27.5 wt black pigment, 50.5% acrylic resin and 22 wt % silicone resin excluding solvent. The black pigment comprises (Co,Fe) (Fe,Cr)2 O4 and Ni. The black high temperature emissivity paint is applied to components of gas turbine engines and the gas turbine engine is run at the gas turbine engines normal operating conditions. The component coated with the black high temperature emissivity paint is viewed by an optical pyrometer and the optical pyrometer is used to determine the temperature of the component. The pyrometer measures the energy radiated by the component. The advantage of the black high temperature emissivity paint is that the colour, and hence the emissivity, remain unchanged at temperatures of 1100° C. and greater. This enables the pyrometer to be used without the need to recalibrate the pyrometer to take into account changes in emissivity of the black high temperature emissivity paint. It enables higher temperature use with more accuracy.

Abstract: A fan (22) for a turbofan gas turbine engine (10) comprises a fan rotor (24) carrying a first set of circumferentially spaced radially extending fan blades (28) and a second set of circumferentially spaced radially extending fan blades (30). The second set of fan blades (30) is arranged downstream of the first set of fan blades (28). The hub to tip ratio (R1/R2) of the first set of fan blades (28) is substantially the same as the hub to tip ratio (R3/R4) of the second set of fan blades (30) and the radius (R2) of the radially outer ends of the first set of fan blades (28) is less than the radius (R4) of the radially outer ends of the second set of fan blades (30). This increases the flow area of the fan (22) by about 7% compared to a conventional fan of the same radius and thus increases the mass flow by about 7% and/or increases the pressure ratio.

Abstract: A fastener (31) is disclosed for a first article, for example a tile (29), to a second article for example an outer wall (27) of a wall structure (21, 22) of a combustor (15) of a gas turbine engine (10). The fastener (31) comprises an elongate main part, which may be in the form of a bolt (34). The main part can extend through the first and second articles. The main part defines a cooling pathway (46) therethrough to allow the passage of a cooling gas through the main part.

Abstract: A mounting arrangement (46) for mounting a turbofan gas turbine engine (10) on an aircraft pylon (44). The gas turbine engine (10) comprises a core engine (24) having a core engine casing (26). The mounting (46) comprises a first mounting (48) for mounting the core engine casing (26) on the pylon (44) and a second mounting (50) for mounting the core engine casing (26) on the pylon (44). The first mounting (48) comprises a first hinge adjacent (52) the core engine casing (26) and a second hinge adjacent (54) adjacent the pylon (44). The first hinge (52) is arranged parallel to the axis (S) of the gas turbine engine (10) to form a roll hinge. The second hinge (54) is arranged in a plane perpendicular to the axis (S) of the gas turbine engine (10) to form a pitch hinge. The second mounting (50) comprises a third hinge (56) adjacent the core engine casing (26) and a fourth hinge (58) adjacent the pylon (44).

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: An apparatus and method of 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 introduction and treatment chamber and includes a fluid distribution device adapted to provide a plurality of discrete turbulent sprays that impact in a turbulent manner on the interior surface of the partition wall to then flow downwardly to the open end in a turbulent manner while steam flow upwardly toward a vent located at the top of the treatment chamber; balanced flow of steam is effected by apertured baffles extending between the interior wall of the vessel and the partition wall.

Abstract: A method of producing an angled hole 14 in a workpiece 10 includes the steps of: using a laser beam to produce an initial orifice in the workpiece 10; translating the laser beam away from the initial orifice to a starting point at a periphery of the hole 14 to be produced; and moving the laser beam such that it traces an elliptical path on the surface of the workpiece, thus defining the periphery of the hole 14, whilst maintaining the focus of the laser beam on the workpiece surface. The starting point is located in a region of the edge of the angled hole which meets the surface of the workpiece at an obtuse angle.

Abstract: A bleed valve 60 for regulating a fluid flow through a bleed hole 88 defined by a casing 49 of a gas turbine engine 10 compressor 22, the bleed valve 60 comprises a central axis 92, a piston 62 and a static structure 70, the static structure 70 generally surrounds the piston 62, and is arranged to define in axial sequence from the bleed hole 88 first, second and third chambers 82, 84, 86 respectively, the piston 62 comprises a spindle 66, a first end plate 90 slidably sealed against the static structure 70 and a valve face end plate 64 from which walls 68 axially extend, the walls 68 being slidably sealed to the static structure 70, the static structure 70 comprises a radially inwardly extending flange 74, the flange 74 defining an aperture 76 through which the spindle 66 axially extends and is slidably sealed against, the first chamber 82 is in fluid communication with the compressor 22 via pressure balancing apertures 108 defined in the valve face end plate 64, the third chamber 86 is also in fluid communic

Abstract: A variable cycle gas turbine engine (10) includes first and second compressors (18,16), combustion apparatus (20) and first and second turbines (22,24) operable to drive the first and second compressors (18,16) respectively via interconnecting shafts. The capacity of one of the turbines (24) may be varied, for example by means of guide vanes (32) which can be adjusted to reduce or increase a throat area (40) through which air leaves the guide vanes to impact the turbine. The capacity of the turbine may be increased at low engine speeds, to reduce the pressure ratio across the turbine and across the compressor (16) which it drives, thereby improving the surge margin of the compressor.

Abstract: 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 fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).

Abstract: A vibration damping system (8) wherein the system (8) comprises a magnetism generating medium (12) and a magnetism energy dissipating medium (16) whereby, in use, vibration of the magnetism generating medium (12) generates a magnetic field, the magnetism generating medium (12) and the magnetism energy dissipating medium (16) being so disposed with respect to each other that the magnetic field is then dissipated by the magnetism energy dissipating medium (16) thereby damping the vibrations of the magnetism generating medium (12).