Abstract: A fuel distributor valve (19) of a type suitable for use in the fuel supply system of a gas turbine engine is disclosed. The valve comprises: a valve body (22) through which a bore (24) extends between a fuel inlet (22) and a fuel outlet (23); a first valve seat (28) and associated valve member (30) provided across the bore (24), the first valve seat (28) defining at least one fuel-flow-port (26) and the valve member (30) being moveable between a closed position in which it substantially seals against the first valve seat (28) to close the or each fuel-flow-port (26) and an open position in which it is spaced from the first valve seat (28) to permit the flow of fuel through the or each fuel-flow-port (26) in a direction flowing from the fuel inlet (22) towards the fuel outlet (23).

Abstract: A drive mechanism comprising a first sprocket encircled by a tensioned chain and an orbit sprocket arranged to orbit the first sprocket in response to a resynchronisation signal. The orbit sprocket is arranged to displace the tensioned chain relative to the first sprocket. The first sprocket is rotatable and is coupled to an output drive sprocket by the tensioned chain such that the first and output drive sprockets are rotatable in synchronicity, whereby the orbit of the orbit sprocket alters the relative angular orientation of the first and output drive sprockets.

Abstract: A turbine assembly having a bladed turbine wheel and a turbine casing (1000), extending axially of the turbine assembly, radially outwardly surrounding the tips of the blades of the turbine wheel, the casing having at least one radially outwardly extending dummy flange (2100, 2200) off which, in axial direction, one or more cooling manifolds (1100, 1200, 1300), wrapping radially outwardly around the casing, are mounted, the or each cooling manifold being adapted to receive cooling air and to discharge the cooling air radially inwardly towards the casing, for cooling the casing.

Abstract: An apparatus for simulating stresses experienced by a rotor blade root in a complementary disc fixture, especially in gas turbine engines. The apparatus comprises a mounting member for receiving a blade speciman having a root. The mounting member has an aperture for receiving the root of the blade specimen, and blade contacting regions on either side of said aperture for holding said blade specimen in said aperture. The apparatus further comprises an actuator for applying a tension load to said blade specimen. The blade contacting regions are undercut such that there is a gap between said blade contacting regions and a main body of said mounting member, whereby the blade contacting regions are able to deflect outward into said gap when a tension load is applied to the blade specimen.

Abstract: High bypass ratio turbofan propulsion engines are designed with a two-step approach to surviving foreign object damage to the fan assembly. First, a containment system encircling the fan assembly to capture any part of a released fan blade in the event of damage occurring, and two in order to cope with the vibrations resulting from a rotating unbalanced fan assembly the support structure for the bearing of the rotating assembly is constructed with frangible parts to introduce a snubber gap to permit the rotating, unbalanced fan assembly and bearing to orbit thereby to reduce the resulting vibrations. However, in the case of very wide chord fan assemblies, the largest acceptable snubber gap is insufficient to reduce the induced vibrations.

Abstract: A mounting system for use in mounting a gas turbine engine having an engine core to an aircraft comprises an engine support arrangement and front and rear mounting assemblies to mount the engine support arrangement to a casing surrounding the engine core. Each of the front and rear mounting assemblies comprises a plurality of circumferentially spaced mounting members to effect the aforesaid mounting of the engine support arrangement to the casing.

Abstract: Utilisation of electrostatic sensor elements is known in relation to obtaining images from a surface such as that of a patient with regard to anomalies including carcinomas. Electrostatic sensor elements, by their nature, are susceptible to creating spurious results in terms of their location with respect to the surface of the subject to be viewed. By providing a visual camera within an array of electrostatic sensor elements the electrostatic charge distribution image is provided by the camera. The image can be overlaid and married with the visual image in a proportionate ratio. In such circumstances an improved final image is provided with inherent visual references to allow analysis of the combined rich display image. A visual camera such as a CCD is used as it is substantially of the same size as the electrostatic sensor elements.

Abstract: A thermal control system for a turbine casing (2) mounted radially outwardly of and circumferentially surrounding blade tips of the turbine blades, the system comprising: one or more circumferential chamber walls (6), each disposed around the casing (2), each to form a circumferential flow chamber (7) radially outward of said surface of the turbine casing (2), each to form a circumferential gap (12) between the circumferential chamber wall (6) concerned and said surface of the turbine casing (2), and the one or more circumferential chamber walls (6) define at least one opening (9) on the radially inward side of the chamber (7) adjacent the surface of the turbine casing (2) such that a thermal fluid injected into the flow chamber (7) concerned may leak out through the circumferential gap (12) via the opening (9), and means to induce circumferential flow on the surface of the casing (2) bounded by the circumferential flow chamber (7) comprising one or more ducts (8) radially outwardly connected to the or each c

Abstract: In certain circumstances recovery of a fluid flow presented through a heat exchanger into another flow can create problems with respect to drag and loss of thrust. In gas turbine engines heat exchangers are utilized for providing cooling of other flows such as in relation to compressor air taken from the core of the engine and utilized for cabin ventilation and de-icing functions. By providing an outlet valve through an outlet duct in a wall of a housing the exhaust fluid flow from the heat exchanger can be returned to the by-pass flow with reduced drag effects whilst recovering thrust. The valve may take the form of a flap displaceable into the by-pass flow before an exit plan to create a reduction in static pressure drawing fluid flow through the heat exchanger.

Abstract: A fiber reinforced metal compressor disc includes a hub, a rim and a diaphragm extending radially between the hub and the rim. The fiber reinforced metal compressor disc comprises a first ring of ceramic fibers and a second ring of ceramic fibers. The first ring of fibers is arranged in the hub and the second ring of fibers is arranged in the rim of the disc. The rim of the disc carries a plurality of blades. This arrangement of the rings of fibers minimizes the weight of the disc, especially for large radius discs suitable for carrying large blades and operating at high rotational speeds.

Abstract: A bearing housing is disclosed herein. The bearing housing includes a chamber with out-take for oil scavenging. The out-take extends across a chordal arc of the chamber. A portion of an outer wall adjacent to the out-take has a spiral divergence.

Abstract: A flow control arrangement is provided for a gas turbine engine in which an inlet slot is positioned prior to a stationary structure such as a stator or pylon in order that air flow is bled or removed from a mainflow. The removed air passes through a passage duct and is re-injected through an outlet nozzle with an askew angle consistent with an angle of rotor blades of a turbine. In such circumstances, distortion in the flow due to the stationary structure is relieved such that there is less instability downstream from that structure.

Abstract: Cooling with regard to high-pressure turbine platforms is important in order to maintain gas turbine engine efficiency. Cottage Roof dampers located below junction gaps between adjacent platforms have been used but tend to present spent coolant flow at a high angle relative to hot gas flows about the aerofoil blades. The present arrangement has the junction gap angled such that the emergent coolant flow remains adjacent to the suction side to create a coolant film lingering above that suction side of the platform.

Abstract: With highly loaded rotors and stators problems can occur with secondary flows sweeping low momentum fluid across the blades reducing efficiency. By provision of collector slots to collect the secondary air and direct that air to a return slot in a rotor hub it is possible to provide impetus to the collected secondary flow to an outlet slot such that there is dispersal of the secondary flow and therefore reduce the effects upon the overall performance of a gas turbine engine incorporating the arrangement.

Abstract: A sealing assembly (100) for providing a seal between a first element (104) and a second element (106), the first element being movable with respect to the second element, wherein the sealing assembly comprises: a sealing member (102) adjacent to the first and second elements; a first seal portion (108) for providing a first seal between the sealing member and the first element, the first seal portion being arranged in a first direction; and a second seal portion (112) for providing a second seal between the sealing member and the second element, the second seal portion being arranged in a second direction, wherein the first direction is arranged at an angle with respect to the second direction and the sealing member is disposed such that the sealing member is movable relative to the second element in the second direction.

Abstract: A cooled aerofoil for a gas turbine engine has an aerofoil section with pressure and suction surfaces extending between inboard and outboard ends thereof. The aerofoil section includes first and second internal passages for carrying cooling air. The aerofoil section further includes a plurality of holes in the external surface of the aerofoil section which receive cooling air from the internal passages. The external holes are arranged such that cooling air exiting a first portion of the external holes participates in a cooling film extending from the leading edge of the aerofoil section over said pressure surface and cooling air exiting from a second portion of the external holes participates in a cooling film extending from the leading edge over said suction surface. The first portion of external holes receives cooling air from the first internal passage, and the second portion of external holes receives cooling air from the second internal passage.

Abstract: A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.

Abstract: A casting arrangement for the single crystal casting of a component in which a common feed for molten metal is provided with a filtration arrangement that incorporates an annular filter. Outlets in a housing surrounding the filter direct the filtered molten metal on to a seed crystal and into a spiral grain selector.

Abstract: An apparatus for characterising the fragmentation of a body following impact with a surface, particularly the fragmentation of a bird following impact with part of an intake of a gas turbine engine, comprises a gun, a target plate, a soft recovery plate across which the body's trajectory can be tracked, and a soft recovery system, characterised in that damage to the body is caused substantially only by the impact on the target plate.

Abstract: Shaped metal deposition apparatus comprises a mounting head for mounting a shaped metal deposition device, an inert gas shield for providing an inert atmosphere around shaped metal deposited in use by the shaped metal deposition device, and a rotatable coupling between the mounting head and the inert gas shield to permit relative rotation therebetween.