Abstract: A ducted fan gas turbine engine (10) is provided with a fan (12) which is carried by a shaft (16). A frangible support member (27) maintains a coaxial relationship between the shaft (16) and the longitudinal axis (15) of the engine (10). In the event of severe damage to the fan (12), the frangible member (27) fractures, allowing the shaft (16) carrying the fan (12) to orbit about the engine longitudinal axis (15). A resilient support member (33,45) exerts a radially inward restoration force on the shaft (16) carrying the fan (12) to reduce vibration.

Abstract: A gas turbine engine combustion chamber comprises a primary combustion zone and a secondary combustion zone downstream of the primary combustion zone. A catalytic combustion zone is arranged downstream of the secondary combustion zone and a homogeneous combustion zone is arranged downstream of the catalytic combustion zone. A pilot injector supplies fuel into the primary combustion zone. At least one primary premixing duct has a plurality of primary fuel injectors to supply a first mixture of fuel and air into the primary combustion zone. A secondary premixing duct has a plurality of secondary fuel injectors to supply a second mixture of fuel and air into the secondary combustion zone. A plurality of temperature sensors are arranged at the intake to the catalytic combustion zone and a processor controls the valves which adjust the supply of fuel the fuel injectors to ensure that the temperature at the intake to the catalytic combustion zone remains in a predetermined temperature range.

Abstract: A ducted fan gas turbine has a fan shaft which is supported at its upstream end by a bearing. In the event of damage to the engine's fan, frangible bolts fracture to permit radial movement of the shaft. That movement is limited by the sequential engagement of the outer race of the bearing with first and second movement limiting portions on fixed structure of the engine. This alters the natural frequency of vibration of the fan, so permitting the fan to windmill without excessive vibration.

Abstract: A gas turbine engine has an assembly of circumferentially spaced rotor blades each having a radial tip. A plurality of seal segments mounted for radial movement circumscribe the rotor blades. Each segment is connected to the casing through a seal carrier provided with a flexible membrane which divides high pressure air from low pressure into two channels.

Abstract: A stator vane assembly for a gas turbine engine (10) compressor (16) comprises a plurality of circumferentially arranged stator vanes (44A) and a plurality of circumferentially arranged load bearing struts (46). The leading edges (45,47) of the stator vanes (44A) and the struts (46) are arranged in a common plane. The leading edges (45,47) of the stator vanes (44A) and the struts (46) have substantially the same profile. The spacing (B) between adjacent struts (44A) in any group is the same.

Abstract: A ducted fan gas turbine engine is provided with a fan which is carried by a shaft. Frangible fuse pins maintain the shaft carrying the fan coaxial with the engine longitudinal axis. In the event of severe fan damage, the fuse pins fracture and the fan shaft orbits about the engine longitudinal axis. A spoked resilient member is provided to exert a radially inward restoration force upon the fan shaft following such an event in order to reduce vibration.

Abstract: A wagon assembly for use in gardening and lawn care comprises a wagon body structure which provides a main compartment. The main compartment accommodates the carriage of items and materials used in gardening and lawn care. A handle structure is pivotally connected to a forward end of the wagon body structure such that the handle structure moves between a stacking position and a range of operating positions. Wheel structures are rotatably connected to the wagon body structure and are constructed to enable the wagon assembly to be rolled manually by exerting force on the handle structure. Upwardly facing supporting surfaces are constructed and arranged to support a first similar wagon assembly aligned above the wagon assembly in a stable stacking and nesting relation with the handle structure of the wagon assembly in the stacking position such that portions of wheel structures of the first similar wagon assembly are disposed between upper peripheral edges of the wagon body structure.

Abstract: A ducted fan gas turbine engine is provided with a fan which is carried by a shaft. Frangible fuse pins maintain the shaft carrying the fan coaxial with the engine longitudinal axis. In the event of severe fan damage, the fuse pins fracture and the fan shaft orbits about the engine longitudinal axis. An annular resilient member is provided to exert a radially inward restoration force upon the fan shaft following such an event in order to reduce vibration.

Abstract: The fan duct of a ducted fan gas turbine engine is provided with a secondary duct at least partly within the downstream end of the primary duct. The secondary duct is provided with means such as flaps whereby the airflow therethrough may be varied to suit flight requirements of an associated aircraft, in a way which will control the maximum diameter of the free stream tube airflow at the intake of the engine, thus effectively reducing the frontal area of the fan duct, and therefor, drag.

Abstract: In a gas turbine engine, compressor delivery air is fed into air inlets in hollow turbine nozzle guide vanes, and then ejected into the gas stream via holes in the vane walls. Valving is provided so as to provide modulation of the cooling airflow over and above the modulation achieved by compressor output when it changes with engine power setting. Excessive cooling of the gas stream is thus prevented.

Abstract: It is the norm to make diffusion bonded and superplastically formed heat exchanger panels from a trio of three sheet stacks, which employs four diffusion bonding stages and three superplastic forming stages. The concept described and claimed obviates one sheet from the central stack and provides only one passageway between the remaining two sheets. The advantages gained include less material and one bonding/superplastic forming stage is obviated with resulting savings in cost, time and machine utilization.

Abstract: A turbine (10) for a gas turbine engine includes an annular array of turbine aerofoil blades (12) which are mounted on a disc (19). Each of the aerofoil blades (12) is provided with a radially inner platform (21). Each platform (21) includes a passage (37) into which leaked cooling air flows. The passages (37) are disposed in a direction having a circumferential component so that cooling air is exhausted from them in a direction that is generally opposite to that in which the disc (19) operationally rotates.

Abstract: An apparatus (14) for locating a source of acoustic mission in an article (10) comprises a plurality of spaced transducers (18) which supply output signals corresponding to detected acoustic emission activity to a processor (24). Artificially induced acoustic emissions (12) are generated in the article (10) by directing a laser beam (33) onto the article (10). A camera (40) produces an image of the article (10) and any laser flashes. A processor (42) converts the positions of the laser flashes to coordinates on the article (10). A processor (24) analyses parameters of the acoustic emission in the output signals and the coordinates of the laser flashes to infer the mathematical relationship between the parameters and location of acoustic emissions.

Abstract: A bladed rotor and surround assembly comprising an annular casing, a bladed rotor element that is rotatable about an axis concentrically within the casing, and an annular shroud liner. The shroud liner, typically made up of an annular array of circumferentially abutting shroud liner segments, is disposed within the casing in an annular radial space defined between the casing and an outer circumference of the bladed rotor. The shroud liner segments have location members to locate each segment within the casing. The location members and the annular radial space are configured to enable axial insertion of the shroud liner segment between the bladed rotor and the casing. In addition the location members and the annular radial space allow a limited amount of radial translation of the shroud segment during insertion. The location members also provide a positive radial location to prevent radial translation of the shroud segment once each shroud segment is in a final assembled position.

Abstract: Method and apparatus for measuring distance includes a capacitance probe positioned adjacent a rotating member and within the housing of the rotating member such that the distance between the probe and rotating member can be measured. The rotating member and probe co-operate with each other so as to define a capacitor. An oscillator comprising a transmission line is electrically connected to the probe, the resonat frequency value of which is a function of the capacitance of the capacitor. The change in distance between the rotating member and the probe can therefore be measured.

Abstract: A method and apparatus of applying a coating to an article having one or more recesses or through holes includes establishing in a bath of coating solution a substantially uniform velocity flow field over and generally parallel to the surface of the article so as to create a pressure differential between the liquid flowing over the surface and the liquid present in the hole or recess.

Abstract: A variable diameter shroud ring (21) for the turbine of a gas turbine engine (10) comprises a support structure (25) which carries an annular array of circumferentially spaced apart ceramic segments (26). The radially outer surfaces of the segments (26) are overlaid by a plurality of circumferentially extending metallic sheets (38). The sheets (38) serve to inhibit gas leakage through gaps between the segments (26) as the diameter of the shroud ring (21) is varied.

Abstract: A tag applicator for cylindrical objects is provided with an applicator station for receiving an adhesive surfaced label or tag over a pair of flexible wrapping fingers; a transport device engages, grips and moves an article to be tagged from a supply station through a tag applying station and then to a discharge station with the movement of the part through the tag applying station being effective in combination with the wrapping fingers to securely apply the adhesive tag to the part.

Abstract: A reciprocating engine (10) comprises separate cylinders (12 and 15) for air compression and expansion with heating of the compressed air taking place in a heat exchanger (17) or combustor (64) located between the cylinders (12 and 15). The flow of gas into the expander cylinder (15) is controlled by an admission valve (37). The stem (41) of the admission valve (37) extends transversely across the expander cylinder (15) and is cooled by the flow of exhaust gases out of the expander cylinder (15).

Abstract: A method of coating a component (6) having at least one passage (16) entirely therethrough. The method comprising the steps of applying a coating (28) to a region of the surface (22) of the component (6), adjacent to one end of the passage. Then directing a liquid jet (38) through the other end of the said passage (16) so as to remove at least a portion of any coating material (28) located within, or obstructing, the passage (16). In this method the jet is channelled by a first portion (42) of the passage (16) before it encounters the coating material (28) within, or obstructing, the passage (16). In particular the jet (38) is a water jet, which is used to remove a ceramic coating (28) from a component (6). The method has particular use in clearing cooling holes (16) within combustor components or turbine blades. The method can also be used in the repair of such components (6).