Abstract: A connection plate for a continuum arm robotic, the connection plate having a collar for connecting to a continuum arm robot and a cut out section from one end and which extends to a plurality of apertures that are present within a face of the connection plate. A continuum arm robot including a robotic arm and a connection plate wherein the robotic arm includes a connection plate that connects to the end of the distal end of the continuum arm robot through a collar, the connection plate having a cut out section that extends from one end into a plurality of apertures that the distal end of the tendons passes through.

Abstract: A method for cleaning a surface of a component includes placing a volume of a cleaning agent onto the surface of the component. The method further includes performing a repair operation of the component either before or after placing the volume of the cleaning agent. The repair operation results in a generation of contaminant particles. Upon contact of the cleaning agent with the contaminant particles, the cleaning agent absorbs the contaminant particles by adhesion. The method further includes removing the cleaning agent from the surface of the component after the contaminant particles are absorbed by the cleaning agent.

Abstract: An actuator pack for a continuum arm robot, the actuator pack including a plurality of actuator pack sections, with each section having a housing and an interface plate, each section further containing a bank consisting of a plurality actuators that are connected to their own respective drive electronics and the actuators being mounted to the housing or the interface plate and having their drive heads exposed through a hole in the interface plate, and wherein the sections of the actuator pack are configured to coupled together in one state.

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine is provided that has high efficiency together with low noise, in particular from the jet flow exiting the engine and the turbine. The combined contribution of the jet and the turbine to the Effective Perceived Noise Level (EPNL) at a take-off lateral reference point, defined as the point on a line parallel to and 450 m from the runway centre line where the EPNL is a maximum during take-off, is in the range of from 3 EPNdB and 15 EPNdB lower than the total engine EPNL at the take-off lateral reference point.

Abstract: An additive manufacturing system includes an energy source and a material delivery device. The energy source is configured to direct an energy beam toward a component to form a melt pool. The material delivery device is configured to feed a wire toward the melt pool to deposit material on the component. In some examples, the material delivery device is configured to discharge a current to the wire to disengage the wire from the melt pool. In some examples, the material delivery device is configured to measure an arc voltage between the wire and the component.

Abstract: The disclosure relates to an electric drive system for an aircraft and to a corresponding operating method. The electric drive system includes a multiplicity of electric thrust generators, wherein each electric thrust generator has an electric motor, and a subsystem group including a multiplicity of subsystems. The thrust generators are apportioned unambiguously between the subsystems so that each subsystem includes two or more of the thrust generators. Furthermore, a control system for operating the drive system is provided, wherein the control system is configured to operate the drive system in such a way that, at least in the event that one of the subsystems of the subsystem group is faulty, an overall yawing moment which is composed of the sum of the yawing moments of the thrust generators of each non-faulty subsystem of the subsystem group essentially disappears.

Abstract: A method for the removal of debris (75) from an aperture (60), the aperture comprising a first aperture diameter (64) and extending along a first axis (62) over a first distance (63), the method comprising the steps of aligning a beam of energy (80) with the first axis such that the beam of energy is coaxially aligned with the aperture, the beam of energy comprising both an energy sufficient to remove the debris, and a first beam diameter (82) which is less than the first aperture diameter; and, exposing the debris to the beam of energy in order to remove the debris from the aperture.

Abstract: A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system to supply oil to the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

Abstract: A method for operating an internal combustion engine with a high pressure accumulator for a fuel injection system, includes the steps of: monitoring, in a time-dependent manner, a high pressure in the fuel injection system; conducting a check, at a high pressure-dependent starting time point, as to whether a continuous injection detection is to be carried out; and checking whether a high-pressure oscillation has occurred within an oscillation time interval prior to a starting time.

Abstract: A gas turbine engine for an aircraft having an engine core configured with a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, the fan comprising a plurality of fan blades, with a nacelle surrounding the gas turbine engine, and a bypass duct outlet guide vane extending radially across the bypass duct between an outer surface of the engine core and the inner surface of the nacelle. An outer wall axis is defined joining the radially outer tip of the trailing edge of the bypass duct outlet guide vane and the rearmost tip of the inner surface of the nacelle. An outer bypass duct wall angle is defined as the angle between the outer wall axis and the centreline, and the outer bypass duct wall angle is in a range from ?15 to ?2.5 degrees.

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

Abstract: A power plant assembly, including—a turbine for driving at least one rotor shaft; —a combustion chamber for generating drive energy for the turbine; —at least one electric machine which is coupled to the rotor shaft and can be operated both in a generator mode and in a motor mode; —and at least one energy storage system which is connected to the electric machine and can store energy generated by the electric machine when the electric machine is in generator mode. A set of control electronics of the power plant assembly is configured to operate the combustion chamber using a lean fuel-air mixture and, for this purpose, to selectively operate the at least one electric machine in generator mode or in motor mode, depending on the power to be applied by the power plant assembly.

Abstract: In a gas turbine engine of the type having a high-pressure (HP) spool and a low-pressure (LP) spool, methods of increasing surge margin and compression efficiency at a given thrust are provided. One method increases compression efficiency and includes transferring mechanical power from the HP spool to the LP spool to reduce a corrected speed of a HP compressor therein and raise a working line of a LP compressor therein. Another method increases surge margin and includes transferring mechanical power from the LP spool to the HP spool to increase a corrected speed of a HP compressor therein and lower a working line of a LP compressor therein.

Abstract: A gas turbine engine comprising a combustor and a fuel management system. The fuel management system comprises a fuel supply line, recirculation line and heat exchanger. The fuel supply line is configured to supply fuel to the combustor. The recirculation line is configured to recirculate excess fuel from the fuel supply line to an engine-located fuel tank via a fuel cooling device. The fuel cooling device is configured to reject heat from the excess fuel in the recirculation line. The heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel management system. The heat exchanger is disposed on the fuel supply line or on the recirculation line. The fuel supply line is configured to receive fuel from an external source and from the engine-located fuel tank.

Abstract: A system and a method for determining a high oil consumption in a gas turbine engine of an aircraft are provided. The method includes determining one or more engine and aircraft conditions. The one or more engine and aircraft conditions includes at least one of an oil quantity, an oil temperature, an oil pressure, an engine speed, an aircraft altitude, and an aircraft attitude. The method further includes determining a trend in oil conditions based on at least the one or more engine and aircraft conditions. The trend in oil conditions provides at least one of a rate of consumption of oil or a time duration of remaining oil. The method further includes determining the high oil consumption based on a comparison of the trend in oil conditions with a threshold or a comparison model.

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.

Abstract: A blower assembly for providing air to an airframe system, including a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier configured to receive and/or direct flow to the rotor; wherein the blower assembly is configured to permit relative movement between the rotor and the flow modifier to move between: a compressor configuration in which the rotor is configured to be 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; and a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate.

Abstract: A transverse flux electric motor includes a stator including coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to produce a torque for driving rotation of the rotor. The transverse flux electric motor has an active parts mass, mact, equal to a cumulated mass of components of the transverse flux electric motor that contribute to the production of the torque. The transverse flux electric motor has an active parts torque density, ?act, defined as a peak rated torque, ?peak, divided by the active parts mass, mact. The transverse flux electric motor has a power factor equal to cos(?), wherein ? is a steady-state phase difference between a stator coil current and a stator coil voltage, and wherein the transverse flux electric motor has a machine parameter ? that is greater than or equal to 65 Nmkg?1, where ? equals ?act/cos(?).

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module. The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.

Abstract: A tie for a component includes a body including an elongate portion and an arch disposed adjacent to the elongate portion. The arch includes first and second middle surfaces extending between a pair of first and second outer curved surfaces, respectively. The body defines a minimum cross-sectional plane perpendicular to a longitudinal axis and passing through the elongate portion. The body further includes a minimum tie width at the minimum cross-sectional plane along a second transverse axis. The minimum tie width is greater than each of a first minimum arch width of the first middle surface and a second minimum arch width of the second middle surface by a width factor greater than or equal to 3 to less than or equal to 10.