Abstract: An apparatus for characterizing 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, characterized in that damage to the body is caused substantially only by the impact on the target plate.

Abstract: A sealing arrangement for sealing between segments of a component assembly. The sealing arrangement includes a sealing member having a mating surface for mating with the surface of the segment. The sealing arrangement further includes a location member removably attached to the sealing member along a transition region therebetween, and also a free end distal to the sealing member. The location member is configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature. The location member is configured to be detached from the sealing member along the transition region and be removed from the segment after the sealing member has been bonded to the segment.

Abstract: A method of inspecting a hole defined by a component situated within an engine, the engine including a chamber configured to receive fluid from a fluid supply, wherein the component is in flow communication with the fluid supply via the chamber, the method includes the steps of: (i) delivering a test fluid via the chamber to the component to induce flow of the test fluid through the hole; (ii) deploying a sensor panel adjacent to the component in a path of test fluid issuing from the hole, the sensor panel being sensitive to impingement of the test fluid; and (iii) assessing a condition of the hole depending on a response of the sensor panel at a location corresponding to the hole.

Abstract: A magnetoplasmadynamic (MPD) generator has a conveying duct shaped for conveying a high velocity, conductive fluid; a magnetic field generator arranged to generate a magnetic field across the conveying duct, substantially perpendicular to the direction of travel of the fluid, such that the fluid passes through the magnetic field when conveyed by the duct; electrodes arranged to conduct a current induced in the fluid as it is conveyed by the conveying duct through the magnetic field; and a fluid break-down circuit arranged to electrically break-down the fluid by developing an additional voltage across the electrodes.

Abstract: Features such as holes in a component which may be an aerofoil component of a gas turbine engine are re-drilled after initial formation, for example to remove blockages created in a coating process. In order to ensure that re-drilling occurs at the precise location of the initial holes, a selected number of the holes are selected, and their exact positions identified, for example by camera imaging and image processing. The actual positions of the selected features are compared with the nominal positions, and an algorithm is generated and then used to calculate the actual positions of the non-selected holes of the array.

Abstract: A diffusion bonded and superplastically formed turbomachine blade, the turbomachine blade comprising: a first layer (4); a second layer (6); and a membrane (2) disposed between the first and second layers (4, 6); wherein the membrane (2) is diffusion bonded to the first layer (4) along a plurality of first strips (10) and the membrane (2) is diffusion bonded to the second layer (6) along a plurality of second strips (12), wherein the first and second strips (10, 12) are offset from one another so that the membrane (2) is bonded to the first and second layers (4, 6) in an alternating pattern; wherein the membrane (2) has a recess (28) which extends into an area between an adjacent pair of first or second strips (10, 12).

Abstract: An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.

Abstract: A joint including a first component and a second component. The second component including a shape memory material component. The first component has a half dovetail shaped slot and the shape memory material second component has a half dovetail shaped attachment feature disposed in the half dovetail shaped slot in the first component.

Abstract: A method of correcting the shape of a brittle cast component such as a low pressure turbine blade. The method includes steps of placing the component against a creep mold having a surface defining the desired profile of the component and HIP treating it to creep deform the component to the desired shape whilst consolidating it and removing gas and shrinkage porosity.

Abstract: A clearance control arrangement includes first and second components defining a clearance therebetween. The first component includes a surface portion having at least a layer of material that changes thickness when actuated. The clearance control arrangement also includes an actuator to actuate the layer of material.

Abstract: A clipping die (102) for clipping a component comprises a riser (104) having a support surface (108) with a cutting edge (110) for clipping the component under the action of a punch (120). A referencing member (112) is provided for engagement with a reference portion of the component. The referencing member (112) is mounted on a resilient element (118). The resilient element (118) is depressed under the action of a punch (120) to move the referencing member (112) into a position such that the component is fully supported by the support surface (108) during the clipping process.

Abstract: An acoustic liner for a gas turbine engine comprises a folded cavity with an opening and a resistive facing sheet covering the opening, characterised in that the folded cavity further comprises a resistive septum that increases attenuation at high frequencies. The presence of the septum permits the attenuation of noise over a much wider range of frequencies than in known liners. By suitable choice of the resistance and reactance of the septum and of its position in the cavity, the liner can provide low frequency attenuation comparable with known liners while also providing improved attenuation at higher frequencies.

Abstract: A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the tiles. Air holes are provided through the wall and the tiles and a flow passage is provided adjacent the air holes. A flow passage is defined by changing the profiles of the air holes in the outer wall and/or the location features to provide a localised gap through which cooling air is directed to cool regions subject to overheating and extend service life.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion including a lid which has a leading edge, a trailing edge and opposing side edges which connect respective ends of the leading and trailing edges. The lid defines an airflow surface for air being drawn through the engine. The annulus filler further has one or more attachment formations which, in use, connect the body portion to the rotor disc. The lid is configured such that the stiffness of the lid under compressive loading exerted on the opposing side edges by sideways blade movement is greater at the leading edge than at the trailing edge.

Abstract: A rim driven electrical machine for interaction with a flow of water, comprising: a rotor mounted within a housing, the rotor including at least one circumferential conductor and a central passageway, the central passageway for receiving at least one blade arrangement for rotational interaction with a fluid within the central passageway, and; a stator supported by the housing and arranged circumferentially around the rotor, the stator including windings for providing a travelling electromagnetic wave for interaction with the at least one circumferential electrical conductor of the rotor, wherein the stator extends only partially around the circumference of the rotor so as to have a first end and a second end separated by an arcuate angle.

Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Abstract: A method and arrangement for detecting failure of an actuated component, particularly a valve. The method comprises determining a calibration step response and an in-use step response for the actuated component, determining any difference between the responses and comparing the difference to a pre-determined threshold indicating failure.

Abstract: A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface.