Abstract: A system for correcting a measured position of a continuum robot whilst inspecting or repairing a component includes at least one first sensor coupled to the continuum robot. The at least one first sensor is configured to generate information related to an orientation of the at least one first sensor relative to a reference point on the continuum robot. The system further includes at least one second sensor associated with the continuum robot. The at least one second sensor is configured to generate information related to a change in a length of the continuum robot. The system further includes a controller that determines a parasitic twist in the continuum robot and corrects the measured position of the continuum robot based on the determined parasitic twist in the continuum robot.

Abstract: A fuel system for a hydrogen fuelled gas turbine engine comprises a tank configured to store hydrogen, a pump configured to provide pressurised hydrogen at an outlet thereof, and a pre-heater configured to heat at least a portion of pressurised hydrogen fuel downstream of the pump. A preheater return offtake is configured to return at least a portion of hydrogen fuel heated by the preheater to the tank.

Abstract: There is provided an electrical machine comprising: a rotor at least partially disposed within a rotor chamber; a stator core coaxially arranged with the rotor chamber; and a stator sleeve. The stator sleeve is annular and is positioned between the stator core and the rotor chamber. The stator sleeve comprises a magnetic material having a relative permeability of at least and an intrinsic coercivity no greater than 1 kAm?1.

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines, including a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A decoking cleaning system for cleaning at least one component in-situ within a combustion engine system, the decoking system including at least one ultrasonic transducer with a means of connecting the at least one ultrasonic transducer to a component to be cleaned within the combustion engine system, the at least one ultrasonic transducer being connected to a power and voltage supply.

Abstract: A rotary assembly for driving spool rotation includes a rotor and a flow modifier. The rotor is mechanically coupled to a spool of a gas turbine engine. The flow modifier receives flow from and/or direct flow to the rotor. The rotary assembly permits relative movement between the rotor and the flow modifier to move between: a turbine configuration wherein the rotor receives air from an external air source to drive the spool to rotate; and a compressor configuration wherein the rotor is driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system. The rotary assembly also includes controller to control relative movement between the rotor and the flow modifier through a range of turbine positions of the turbine configuration to vary a torque applied to the rotor for driving the spool.

Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft, and can output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft.

Abstract: A woven structure formed by warp and weft tows A, E of fiber reinforcement material includes: a plurality of multi-warp stacks SA, each including a plurality of warp tows A which are in superposition along a longitudinal extent of the warp stack SA, a plurality of multi-weft stacks SE, each including a plurality of weft tows E which are in superposition along the stack SE, wherein one or more multi-warp stacks SA and/or one or more multi-weft stacks SE has an embedded taper structure, including: an embedded tow A1, A2, E1, E2 which has a terminal portion M1, M2 disposed between two locally outermost tows A0, E0 of the respective stack SA SE, the terminal portion M1, M2 terminating at a taper position D1 D2 along the respective path of the stack SA SE; and a method for manufacturing a composite component.

Abstract: The disclosure relates to a stator assembly for an electric machine. Example embodiments disclosed include a rotor assembly for an electric machine, the rotor assembly comprising: a rotor core; a plurality of magnets arranged around the rotor core; and a cylindrical rotor sleeve surrounding the plurality of magnets, wherein the rotor sleeve comprises a laminated composite material having an array of ferromagnetic pins extending through a thickness of the rotor sleeve.

Abstract: A gas turbine engine for an aircraft includes a fan system having a reverse travelling wave first flap mode, Fan RTW, and including a fan located upstream of the engine core; a fan shaft; and a front engine structure arranged to support the fan shaft and having a front engine structure nodding mode comprising a pair of modes at similar, but not equal, natural frequencies in orthogonal directions; and a gearbox. An LP rotor system including the fan system and a gearbox output shaft arranged to drive the fan shaft has a first reverse whirl rotor dynamic mode, Rotor RW, and a first forward whirl rotor dynamic mode, 1FW. The engine has a maximum take-off speed, MTO. A backward whirl frequency margin of: the ? lowest ? frequency ? of ? either ? mode Fan ? RTW ? or ? Rotor ? RW ? at ? the ? MTO ? speed the ? MTO ? speed may be in the range from 15 to 50%.

Abstract: This disclosure relates to bidirectional current limiting circuits for use in aircraft electric power distribution systems. Example embodiments include a bidirectional current limiting circuit (500a-c) comprising first and second JFETs (501, 502) connected between first and second terminals (503, 504), wherein: the first terminal (503) is connected to a drain of the first JFET (501) and to a gate of the second JFET (502) via a first biasing element (505, 701); he second terminal (504) is connected to a drain of the second JFET (502) and to a gate of the first JFET (501) via a second biasing element (506, 702); and a source of the first JFET (501) is connected to a source of the second JFET (502).

Abstract: An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

Abstract: A seal for sealing a longitudinally extending gap between first and second components includes: a first portion extending in a longitudinal direction configured to bridge the gap between the first and second components, wherein a sealing surface of the first portion is configured to face the first and second components and curved with a first convex section to sealingly contact the first component, a second convex section to sealingly contact the second component, and a concave section between the first and second convex sections; and at least one second portion coupled to the first portion and configured to urge the first portion into engagement with the first and second components, wherein the second portion includes at least one opening configured to fluidically communicate a pressure of a fluid on a first side of the first and second components to a pressure surface of the first portion opposite the sealing surface.

Abstract: Augmenting design variable data associated with a new parameterisation. A first and second set of physical quantities are obtained that are sampled from one or more simulations associated with a source and target parameterisation, defining source and target points in a physics space, for which a distribution is determined. A first set of design variables in terms of the target parameterisation is obtained corresponding to the simulations associated with the target parameterisation, and which define target points in a design variable space. A second set of design variables in terms of the target parameterisation is generated by evaluating source points in design variable space which exist on or within a boundary of the same hypersurface as the target points, and which minimise the difference between the distribution of source points and target points in physics space and the distribution of source and target points in design variable space.

Abstract: A method of analysing a non-contact excitation system for a spin rig includes, calculating a magnetic field per test piece element, integrating the magnetic field over the test piece element surface to get a force per test piece element, performing a Fourier analysis of the forces acting on the test piece element as it moves past the periodic array of exciter elements, calculating the damping added to the test piece element due to magnetic induction, calculating a vibration response of the test piece element as it moves past the stationary array of exciter elements, calculating a transient response of the test piece element where the stationary array of exciter elements is rapidly moved away from the test piece elements, and using the calculated transient response of the test piece element to calculate a required electromagnetic holding force for the array of exciter elements.

Abstract: An additive manufacturing system includes an energy delivery device configured to deliver, a powder delivery device, and one or more thermal sensors configured to measure a temperature of a first portion of the additively-manufactured component and a second portion of the additively manufactured component. The additive manufacturing system includes a computing device configured to receive data indicative of the temperature of the first portion and of the second portion, determine a residual stress of the additively-manufactured component based at least partially on the received thermal sensor data from the first portion of the additively-manufactured component and the received data from the second portion of the additively-manufactured component; and predict final dimensions of the additively-manufactured component based at least partially on the determined residual stress of the additively-manufactured component.

Abstract: An additive manufacturing system includes an energy delivery device to deliver energy to a build surface of a deposit overlying a substrate to form a melt pool in the build surface, a powder delivery device to direct a powder stream toward the melt pool, and a computing device to determine a first set of deposition parameters for an innermost layer of the deposit overlying the substrate, determine a second set of deposition parameters for an inner plurality of layers of the deposit overlying the innermost layer, determine a third set of deposition parameters for an outer plurality of layers of the deposit overlying the inner plurality of layers, and control the energy delivery device and the powder delivery device to deposit the innermost layer, the inner plurality of layers, and the outer plurality of layers based on the respective first, second, and third sets of deposition parameters.

Abstract: A method for determining grain structure in a component includes disposing the component on a support platform. The method includes generating an imaging beam. The method includes rotating and/or revolving an imaging beam source and an imaging beam receiver relative to the support platform. The method includes acquiring, during the rotation and/or revolution a plurality of projections each taken at the imaging beam receiver. The method includes performing reconstruction, by a processor, of first projections and second projections from the plurality of projections to obtain a first three-dimensional image and at least one second three-dimensional image. The first projections are acquired in at least one first angular range and the second projections are acquired in at least one second angular range.

Abstract: This disclosure relates to cooling modules for power electronics converters. Example embodiments include a cooling module (100) for a power electronics converter, comprising: first face (101) having a cooling liquid inlet (102); an opposing second face (103) having a cooling liquid outlet (104); a plurality of side walls (105a-d) extending between the first and second faces (101, 103), each side wall (105a-d) being configured for cooling a semiconductor switching device (1061-6) of the power electronics converter; and a helical cooling channel (107) extending through the cooling module between the cooling liquid inlet (102) and the cooling liquid outlet (104).

Abstract: A gas turbine engine for an aircraft comprises an engine core. The engine comprises a fan located upstream of the engine core. The engine comprises a nacelle surrounding the fan and the engine core and defining a bypass duct, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4. The engine comprises a plurality of actuators and a fuel supply system arranged to supply fuel for combustion in the combustor, and to supply fuel to fueldraulically drive at least one actuator. The fuel comprises at least 25% SAF by volume, and the fuel supply system is arranged such that a peak differential pressure of the fuel across the at least one fueldraulic actuator during cruise conditions is at least 2400 kPa.