Abstract: A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells. Each cell includes an open radially inner end in fluid communication with an interior side of the nacelle, and an open radially outer end in fluid communication with an exterior side of the nacelle. Each open end of each cell defines a respective cross sectional area. The intake liner further comprises radially inner and outer facing sheets overlying a respective radially inner and outer open ends of the respective cell. Each facing sheet defines at least one aperture overlying at least one cell, an overlying portion of the respective aperture having a smaller cross sectional area than the respective open end of the respective cell.

Abstract: A composite structure is provided. The structure is formed of rigid composite material in which non-metallic continuous fibers reinforce a polymer matrix. The continuous fibers are electrically conductive. The structure has electrodes electrically connected to the continuous fibers. The composite material contains one or more insulating barriers which electrically divide the structure so that a first portion of the material in electrical contact with one of the electrodes can be held at a different electrical potential to a second portion of the material in electrical contact with the other electrode. In use, an electrical unit can be provided to electrically bridge the first and second portions of the material such that electrical signals can be transmitted between the electrodes and the electrical unit via the continuous fibers.

Abstract: A vortex detection method is described. The method comprises storing a plurality of points at locations over a region (32) in which vortex detection is to be performed. A value for each of a plurality of fluid flow parameters, such as velocity, pressure and density, is determined at each point. The points are grouped as being contained in either a vortical flow portion or non-vortical flow portion of the region according to one or more statistical distribution for said fluid flow parameters. A point (p) in a vortex core is identified according to the direction of motion of an array of further points (46) relative to said point in the vortex core. The further points (46) may surround the vortex core point.

Abstract: This invention concerns improvements in the polishing of internal surfaces and structures of components, particularly components with a complex internal geometry. Embodiments of the invention use an alternating current electromagnet (48) driven by a signal generator (50) to constantly alter the rheology of the magnetorheological fluid (5). An improved magnetorheological fluid (25,30) is also disclosed.

Abstract: A flow feature detection method is described. The method includes storing a plurality of points at locations over a region in which vortex detection is to be performed. A value for each of a plurality of fluid flow parameters, such as velocity, pressure and density, is determined at each point. The points are grouped as being contained in either a flow feature portion or normal flow portion of the region according to one or more statistical distribution for the fluid flow parameters. A point is identified as being indicative of the flow feature by identifying multiple further points at least partially surrounding the point, and determining a plane in which the flow feature is identifiable based upon the relative values of the one or more fluid flow parameter for the further points. The method may be used to detect vortices and to identify a two-dimensional plane representative of a vortex.

Abstract: A de-oiler for separating oil from an air/oil mixture comprises a housing, and a rotatable porous element accommodated within the housing. The housing has a first axial face and a second, opposite, axial face, the first axial face being separated from the second axial face by an axial length. The housing has an inlet positioned on the first axial face, a first outlet positioned on the second axial face, and a second outlet positioned on a radially outwardly facing surface. In use, the inlet is adapted to receive a first flow comprising an air/oil mixture, and rotation of the porous element separates the oil from the air/oil mixture, with the first outlet being adapted to exhaust a second flow comprising de-oiled air, and the second outlet being adapted to exhaust a third flow comprising separated oil.

Abstract: A damper damping motion of a first object relative to a second object, the damper including: a casing including a conductor; plurality of magnetic elements serially in a first direction within the casing and each including at least one magnet so adjacent magnetic elements repel in the first direction; at least one magnetic element is moveable relative to other magnetic elements within and relative the casing; the conductor allows movement of at least one moveable magnetic element relative to the casing induces current in the conductor, the magnetic field produced by current providing a braking force to the moving magnetic element; at least one moveable magnetic elements includes a first connecting part and either casing or at least one other magnetic element includes a second connecting part, one connecting part for connecting the damper to the first object, and other connecting part for connecting the damper to the second object.

Abstract: The invention concerns an aircraft propulsion system having an engine core within which fuel is combusted to produce an exhaust containing water produced from the combustion of fuel, at least one propulsive fan for generating a mass flow of air which mixes with the exhaust of the engine core, and one or more sensor arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine; and a controller arranged to control the ratio of the mass flow of water in the exhaust to the mass flow of air propulsed by the propulsive fan such that the ratio is reduced upon sensing of said condition by the one or more sensor.

Abstract: A method of determining rotor blade axial displacement (bij). The rotor blade tip (34) comprises first and second measurement features (36, 38) arranged to make an acute angle therebetween. Measure time of arrival (tijk) of the once per revolution feature (1), first and second edges (40, 42) of the first measurement feature (36), and first and second edges (44, 46) of the second measurement feature (38), for at least two revolutions of the rotor (2). Convert these to circumferential distances (dijk) for each revolution. Calculate a feature angle (?ijk) between each measurement feature (36, 38) and the once per revolution feature (1) for each revolution. Calculate blade untwist angle (?ij) from the change in feature angle (?ijk) between measured revolutions. Calculate the rotor blade axial displacement (bij) from the blade untwist angle (?ij) and the circumferential distance (dijk) of the point from one of the measurement features (36, 38).

Abstract: A turbine casing assembly, comprising an annular seal segment assembly for surrounding the turbine adjacent to the turbine blades. An abradable coating is provided on the inboard surface of the seal segments of the assembly and one or more coolant ducts extend from the outboard surface of the seal segment assembly through respective seal segments and the abradable coating, for carrying a coolant towards the blade tips. One or more annular grooves are formed in the inboard surface of the abradable coating, the or each coolant duct opening into one of the one or more annular grooves.

Abstract: A method of controlling the angular orientation of at least one variable fluidfoil. The method includes the steps of receiving detected fluidfoil angular orientation data for the at least one fluidfoil; receiving a fluidfoil angular orientation demand; generating a modified angular orientation demand by modifying the fluidfoil angular orientation demand before it is used to control adjustment of the at least one fluidfoil, the modification being performed using the detected fluidfoil angular orientation data; and outputting the modified demand and controlling the at least one fluidfoil angular orientation in accordance with the modified demand.

Abstract: A molybdenum based alloy composition including between 8.5% and 9.5% hafnium and 0.15% and 0.

Abstract: The present invention provides a sealing element for an air-riding seal system. The seal has a mounting portion for mounting on a rotor and a sealing portion having a sealing face for facing a second sealing element. A bridging portion is provided extending radially between the mounting and sealing portions. The bridging portion allows axial displacement between the mounting portion and sealing portion and/or angular variation of the sealing face relative to the mounting portion and may be a pliable/flexible membrane structure allowing said axial displacement/angular variation by flexing.

Abstract: A gas turbine engine may include a combustor having an inner wall and an outer wall defining a combustion chamber there between. The inner wall and the outer wall may each have at least one opening into the combustion chamber. The gas turbine engine may also include at least one mobile conduit through which a cooling fluid may flow. The mobile conduit may pass through the combustion chamber from the at least one opening in the outer wall to the at least one opening in the inner wall. The gas turbine engine may further include a first joint and a second joint fluidly connecting the mobile conduit to the at least one opening in the inner wall and the at least one opening in the outer wall, respectively. The first joint and the second joint may enable multiple degrees of freedom of the mobile conduit within the combustion chamber.

Abstract: The manufacture of a casing which has a boss includes providing two canister portions a first defining an outer wall geometry of a casing including a boss and a second defining an inner wall geometry of the casing. The casing is made using known PHIP methods. The second canister portion includes an array of holes or recesses which, when the canister portions are aligned, face a recess on the first canister portion which defines the boss such that in the nett shape COS an array of pedestals is provided aligned with the boss. The dimension from an exposed end of a pedestal to an exposed surface of the boss is sufficient to receive a bolt thread of the minimum length required to secure a component to the boss.

Abstract: A fuel manifold and fuel injector arrangement comprises an annular fuel manifold and a plurality of fuel injectors. Each fuel injector comprises a fuel injector head and a hollow fuel feed arm. Each fuel injector has a pipe to supply fuel to the fuel injector head. The pipe extends from the fuel feed arm and through a corresponding aperture in the casing. The annular fuel manifold is arranged around the casing and the annular fuel manifold comprises a plurality of connectors. Each connector has a socket aligned with a corresponding aperture in the casing. Each pipe has a plug arranged to be radially slidably mounted in the socket of the corresponding connector of the annular fuel manifold to allow relative radial movement between the casing and the annular fuel manifold.

Abstract: A gas turbine drive shaft arrangement, comprising: a hollow compressor drive shaft, a first hollow turbine drive shaft for driving a first turbine stage and a second hollow turbine drive shaft for driving a second turbine stage, wherein the compressor drive shaft has a spline on an internal surface that is meshed with a spline on an external surface of the first hollow turbine drive shaft, the first turbine drive shaft further comprising a spline on an internal surface thereof that is meshed with a spline on an external surface of the second hollow turbine drive shaft.

Abstract: A method to determine a fatigue limit for a material. Form a test component including the material. Identify a resonant frequency of the component and an excitation frequency which causes the component to vibrate. Measure a response parameter of the component when excited at the excitation frequency. Test the component to determine its fatigue limit by sub-steps to: apply an excitation force to the component at the excitation frequency to cause vibration of the component; alter the applied excitation force at constant excitation frequency to maintain the response parameter constant; measure at least one of an input parameter and an output parameter; iterate the sub-steps to alter and measure until the first order, second order, or first and second order derivatives of the input parameter and/or output parameter exhibit a discontinuity. Repeat the steps for a different excitation frequency. The fatigue limit for the material includes all the identified discontinuities.

Abstract: A gas turbine engine includes an air intake and propulsive fan that generates two airflows A and B. Gas turbine engine includes, in axial flow A, core including a compressor, first combustor, high pressure turbine including first turbine stage, second combustor, second turbine stage of the high pressure turbine, low pressure turbine and core exhaust nozzle including and divergent portions. Fan housing surrounds the core and fan and defines, in axial flow B, a bypass arrangement including the fan, a duct, a third combustor in the form of a duct burner and a bypass nozzle including a converging portion and a diverging portion. The bypass and core are arranged coaxially, such that the core flow A is exhausted annularly within the bypass flow. When the duct burner is in operation, the exhaust velocity of the bypass flow is greater than the exhaust velocity of the core flow.

Abstract: A gear including an inner bearing part; an outer part including a plurality of teeth; an intermediate part between the inner bearing part and the outer part, the intermediate part including a plurality of support members extending radially between the inner bearing part and the outer part, the plurality of support members being distributed along a longitudinal axis of the gear.