Abstract: A rotary transformer includes a primary core having a primary coil wound thereon, and a secondary core having a secondary coil wound thereon, the cores being mounted for relative rotation about an axis of rotation. The transformer is characterized in that one of the cores includes a plurality of core segments arranged in spaced-apart relation relative to one another in a substantially circular array about the axis, and the other core has a substantially annular configuration. In a particular embodiment, the primary core is fixed and hence remains static during operation, and includes a plurality of spaced apart core segments arranged in a circular array around the axis.

Abstract: A boundary layer energizer (20) for energizing a boundary layer flow (33) over a surface (22), the boundary layer energizer (20) comprising one or more passages (24) terminating in one or more respective holes (26) provided on the surface (22), wherein the one or more passages (24) comprises at least one fin (25) configured so as to generate a vortex flow in the one or more passages (24) such that, when in use, a fluid emanating from the one or more passages (24) flows in a vortex.

Abstract: An open-rotor gas turbine engine comprising a starter/generator, a first spool and a second spool, the second spool is of a lower pressure than the first spool; wherein the starter/generator is connected to the first and second spools via first and second clutches respectively. The method of operating the open-rotor engine comprises the step of supplying power to the starter/generator to drive the first spool via the first clutch to start the engine and, once the engine is self-propelling, a step of driving the starter/generator from the second spool via the second clutch to generate electricity.

Abstract: A magnetic gear arrangement includes: a first gear member for generating a first magnetic field, a second gear member for generating a second magnetic field, and a coupling device which provides an arrangement of interpoles between the first gear member and the second gear member. The interpoles couple the first and second magnetic fields to produce a gearing between the first and second gear members. The first gear member has superconducting magnets or coils for generating the first magnetic field and/or the second gear member has superconducting magnets or coils for generating the second magnetic field.

Abstract: A component such as a pressure vessel includes a cladding layer bonded to a substrate by a welding process. The component is inspected by a method that includes using a first camera to record a first image of an inspection portion of the cladding layer, the inspection portion having a pattern of markings; causing or allowing a temperature change in the component; using a second camera to record a second image of the inspection portion; and identifying the deformation of the pattern of markings on the inspection portion by reference to relative movement of the respective markings between the first and second image. The temperature change may occur as a result of cooling of the component after the welding process. Analysis of the deformation may be conducted by a Digital Image Correlation process, enabling possible defects or flaws in the component to be identified.

Abstract: A hydraulic fluid transfer coupling has a stator, a first coaxial rotor, and a second coaxial rotor. The first rotor is radially inwards of the stator, the second rotor is radially outwards of the stator, at least part of the first rotor axially overlapping with the stator, and at least part of the second rotor axially overlapping with the stator. The first rotor carries one or more first rotating fluid lines, and the second rotor carries one or more second rotating fluid lines. The stator carries one or more first static fluid lines and second static fluid lines. Each pair of a first rotating fluid line and the corresponding first static fluid line are fluidly coupled and each pair of a second rotating fluid line and the corresponding second static fluid line are fluidly coupled. Hydraulic fluid is transferable between each static fluid line and the corresponding rotating fluid line.

Abstract: A first element (10) adapted to selectively engage a second element (20), wherein the first element comprises a coating (12) and at least an engaging portion (14) of the first element is coated in said coating, wherein the coating is formed by vapour deposition to provide a thermo-chemically stable layer for temperatures up to 800° C. The coating (12) may comprise one or more of a nitride, oxide or carbide of titanium, chromium or aluminium.

Abstract: An electrical generating system for aircraft with one or more engines includes a plurality of generators associated with the engines so as to produce respective AC outputs. The frequencies of these outputs can differ from each other, as a result of differing engine speeds and/or deliberate design, but they are to be connected to a common bus to avoid redundancy of wiring. One or more converters are present between the generators and the bus for adjusting the output frequency of the generators to provide an AC output voltage at a common bus frequency. The system includes a control system for setting the AC bus frequency in such a way that it can vary with time. The bus frequency may follow the natural frequency of the engine, and only small converters are needed to make the already approximately equal generator frequencies identical, so that they can all feed the common bus.

Abstract: A method of determining the quality of a friction weld between two components, the method comprising joining two components together using a friction welding process, measuring the loss of length of the components as a function of time during the friction welding process, determining the double differential with respect to time of the loss in length of the components as a function of time, determining the quality of the friction weld by calculating the R2 value of the linear fit to the loss in length of the components as a function of time over a defined time period, determining the end of the defined time period by identifying the start of the final positive peak of the double differential with respect to time of the loss of length of the components as a function of time, calculating R2 from the least square difference of the linear fit over the defined time period of the loss of length of the components as a function of time and comparing the calculated value of R2 with acceptable values of R2 to determine

Abstract: Mounting of gas turbine engines in aircraft requires use of thrust struts associated with mountings. It is important should there be failure that a load path is maintained. Furthermore, on a wing or in-situ inspection is highly desirable with respect to reducing maintenance costs. Of particular concern is failure as a result of cracking both sideways and vertical which may result in loss of all load paths through the mounting. By provision of independent cranks which are associated through crank pivots in apertures of the cranks and then articulation about central pivots provided in apertures and a central element along with pivot association of the struts through pivots created about apertures in the cranks load paths are maintained. By independent provision of the cranks sideways and vertical cracking cannot cause failure in both load paths to the arrangement from the struts.

Abstract: An electrical machine comprising: a first stator member (16) having a field magnet (22); a second stator member (18) forming an armature, the second stator member (18) being spaced from the first stator member (16); and a pair of contra-rotatable rotors (12a, 12b) disposed between the first and second stator members (16, 18); wherein at least a portion (14) of each of the rotors (12a, 12b) is magnetisable so as to transmit magnetic flux between the field magnet (22) and the armature.

Abstract: A heat exchanger is provided for warming fuel prior to introduction of the fuel to an engine, the heat exchanger including: a fuel inlet and a fuel outlet; a heat exchange matrix having heat transfer components past which the fuel flows between said inlet and said outlet and which are arranged to be heated; and swirl inducing means arranged between said inlet and said matrix arranged to cause fuel from said inlet to swirl prior to entering said matrix. By causing the fuel to swirl prior to entering the heat exchange matrix, entrained ice in the fuel can be caused to concentrate at an outer region of the heat exchanger thereby allowing fuel to continue to flow through the heat exchanger to the engine even when ice is present in the fuel.

Abstract: A heat treatment apparatus 10 for heat treating metals or metallic components includes a fluidised bed furnace 20 and a removable insert 30 which is accommodated within the fluidised bed 50 of the furnace 20. The removable insert 30 enables the geometry of the fluidised bed 50 to be optimised with respect to the size and shape of a component 70 which is to be heated.

Abstract: A heat and/or fire protection assembly for a component, the assembly comprising: a plurality of protrusions distributed about a surface of the component, the protrusions protruding with respect to the surface of the component; the protrusions comprising a barrier material, the barrier material being arranged and configured to form a first protective layer under the action of heat, the first protective layer being arranged to protect the component from the heat.

Abstract: A mounting assembly for attaching a ducted fan gas turbine engine that includes an intake, a propulsive fan, a fan case surrounding the fan, and a core engine. The air intake is attached to the front of the fan case such that loads acting on the air intake are transmitted to the fan case. The mounting assembly includes: a support structure extending in an axial direction of the engine and having a rearward region adapted to attach to the aircraft; and a load distribution ring coaxial with and rearward of the fan case, adapted to join to the fan case, and joined to a forward region of the support structure. The support structure and the load distribution ring are adapted such that the primary load path for the loads transmitted to the fan case by the air intake is through the load distribution ring and the support structure.

Abstract: A joint assembly includes a first component with a flange containing a plurality of spaced through-holes; a second component with a joining portion having an end surface which faces the flange and containing a plurality of spaced elongate cavities; and a plurality of fixation devices. Each cavity extends into the joining portion from the end surface in alignment with one of the through-holes. Each fixation device includes: a bolt which extends through a respective through-hole and the corresponding cavity, and includes a nut which is embedded within the joining portion at the corresponding cavity to receive the bolt such that on tightening the nut and bolt a clamping force is exerted across the flange and the end surface to join the first and second components together. Under axial loads less than that causing bolt failure, each fixation device is deformable to remove the clamping force.

Abstract: Utilization 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 noise reduction device, for example for use in a bleed assembly of a gas turbine engine, comprises partitions having apertures which provide contractions and sudden expansions of flow passing through the device, turbulators being provided between the partitions to break up jets issuing from the Apertures. Breaking up the jets before impact with the partitions enables the partitions to be disposed closer together, so enabling adequate noise reduction to be achieved in a device of relatively small thickness.

Abstract: It is necessary to support and manipulate such bulky items as gas turbine engines through appropriate cradle arrangements. It is necessary to allow robust presentation of the gas turbine engine upon a base such that it can be lifted to a position whereby the engine can be rotated to adjust the configuration of the engine within an arrangement. Such manipulation may minimize height or width dependent upon requirements. By provision of lever assemblies comprising lever arms linked together through a pivot link and a cross link rotation by an actuator of one assembly gives consistent presentation of the locator elements defining a center of rotation for the engine. The arrangement can be locked in a lowered condition for transportation or lifted to allow rotation and re-orientation of the engine with regard to external protuberances to limit width or height.

Abstract: A weld enclosure and welding apparatus including a weld enclosure. Also a method of welding. The apparatus has first and second opposed tooling faces adapted to receive and hold respective first and second weld elements. The weld enclosure comprises a housing that allows relative movement between the weld elements and a change in a physical dimension of at least one of the weld elements. The weld enclosure also comprises locating means for locating the housing relative to the welding apparatus and includes heating means.