Abstract: A method of controlling at least one of a first robot and a second robot to collaborate within a system, the first robot and the second robot being physically separate to one another, the method including: receiving sensed data associated with the second robot; determining position and/or orientation of the second robot using the received sensed data; determining an action for the second robot using the determined position and/or orientation of the second robot; and providing a control signal to the second robot to cause the second robot to perform the determined action to collaborate with the first robot.

Abstract: A mounting bracket for mounting an accessory to a gas turbine engine comprises a space frame structure. The space frame structure comprises a plurality of struts joined to one another at nodes.

Abstract: A system for operating a gas turbine engine to mitigate the risk of ice formation within the engine, the system including a controller arranged to control at least one operational parameter of the engine such that the engine operates in a safe zone; and, a processor configured to function as a determining module to make a comparison between values and determine whether the engine is operating within a safe zone based on at least a core pressure parameter relating to the pressure within the engine and a core temperature parameter relating to the temperature within the engine, wherein the safe zone is defined by the product (multiplied) of the core pressure parameter and core temperature parameter being above a safe threshold.

Abstract: A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

Abstract: Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.

Abstract: A method of determining the location of a fault within a first inductive part of an electrical circuit, including a voltage source, first inductive part and second inductive part. A shortened circuit created by the fault includes the voltage source, a portion of the first inductive part and the second, connected in series. The fault occurs across first and second points in the first inductive part. The length of first inductive part between a positive terminal and first point is substantially equal to the length of first inductive part between a negative terminal and second point. The voltage source supplies a known voltage Vs when the fault occurs and the second inductive part has a known inductance L2 when the fault occurs. The method takes advantage of the initial transient response of the circuit to determine the inductance of the portion of the first inductive part in the shortened circuit.

Abstract: A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

Abstract: A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a planet gear carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. Each planet gear is rotatably mounted in the planet gear carrier. The planet gear carrier comprises a plurality of axles arranged parallel to the axis of the gearbox. The axially spaced ends of each axle are secured to the planet gear carrier. Each planet gear is rotatably mounted on a corresponding one of the axles by a bearing arrangement. Each bearing arrangement comprises a journal bearing and a rolling element bearing and each planet gear is rotatably mounted on a journal bearing and each journal bearing is rotatably mounted on an axle by at least one rolling element bearing.

Abstract: A stator vane arrangement for a turbomachine comprises a radially inner annular structure, a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the inner annular structure and the outer annular structure. At least one of the vanes has a passage extending from the inner annular structure to the outer annular structure. The inner annular structure has at least one radially inwardly extending boss and each boss has a passage extending there-through. The passage in each boss is aligned with a corresponding passage in a vane. Each boss comprises a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area. The first portion of each boss is positioned between and interconnecting the second portion of the boss and the inner annular structure.

Abstract: A rotor assembly (30) comprising a rotor (32) having an annular array of rotor blades (34), the rotor mounted to a shaft (38). A phonic wheel (40) coupled to the shaft. A speed sensor (44) axially aligned with the phonic wheel and configured to measure voltage (V), amplitude of the voltage being proportional to clearance (46) between the sensor and phonic wheel. A processor (48) configured to: receive the voltage measurement; derive shaft speed (?) from the voltage measurement; identify modulation of the voltage amplitude at a frequency which is an integer multiple of the shaft speed; compare voltage amplitude to a threshold; and output a rotor damage signal based on the comparison.

Abstract: A method of controlling a robot within a volume, the method comprising: receiving a three dimensional model including a model of the robot and a model of the volume in which the robot is configured to move within; defining a plurality of positions within the model of the volume to which the robot is moveable to, the plurality of positions being identified by an operator; receiving scanned three dimensional data of the robot and at least a part of the volume; determining a transformation algorithm using the three dimensional model and the scanned three dimensional data; applying the transformation algorithm to one or more positions of the plurality of positions to provide one or more transformed positions; and controlling movement of the robot using one or more of the transformed positions.

Abstract: A method of laser drilling a hole comprising providing a laser source at a first side of a component to laser drill a hole through the component. A light source is positioned in the path of the laser beam at the opposite side of the component. A camera is provided at the first side of the component. The camera is positioned such that it has a line of sight view of the light source through the laser drilled hole. The laser drilled hole in the component is viewed using the light provided by the light source at the opposite side of the component. The parameters of the laser drilled hole are measured using the view of the laser drilled hole provided by the camera and a flow of gas is provided over the surface of the light source to protect the light source.

Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.

Abstract: A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.

Abstract: A gas turbine engine (10) comprises: a low pressure compressor (18) comprising a centrifugal compressor stage (24); a low pressure turbine (44) configured to drive a load (12), the low pressure turbine (44) being provided rearwardly of the low pressure compressor (18); a high pressure turbine (42) provided rearwardly of the low pressure turbine (44); a combustor (40) provided rearwardly of the high pressure turbine (42); a high pressure compressor (32) provided rearwardly of the combustor (40); and an intercooler heat exchanger (28) configured to exchange heat between core airflow (B) exiting the low pressure compressor (18) and fan airflow (A), wherein the high pressure turbine (42) and high pressure compressor (32) are coupled by a high pressure shaft (46), and the low pressure turbine (44), low pressure compressor (18) and load (12) are coupled by a low pressure shaft (22).

Abstract: An aircraft gas turbine engine includes a fan arranged to be driven by a gas turbine engine core. The core includes a first core module including a first compressor and a fan drive turbine interconnected by a first shaft, and a second core module including a second compressor and a second turbine interconnected by a second shaft, the first and second core modules being axially spaced. The gas turbine engine further includes an intercooler arrangement configured to cool core airflow between the first and second compressors, the intercooler arrangement including a cooling air duct provided in heat exchange relationship with a compressor duct provided between the first and second compressors, the cooling air duct including a fan air inlet configured to ingest fan air downstream of the fan, wherein the cooling air duct includes a flow modulation valve configured to modulate air mass flow through the fan air inlet.

Abstract: An aircraft gas turbine engine (110) comprises first and second non-coaxial propulsors (113a, 113b), each propulsor (113a, 113b) being driven by a common gas turbine engine core (176) comprising a propulsor drive turbine (143) arranged to drive the first and second propulsors (113a, 113b) via a propulsor drive coupling (127). The core (176) further comprises a first core module (190) comprising a first compressor (129) and a first turbine (131) interconnected by a first shaft (177), and a second core module (191) comprising a second compressor (128) and the propulsor drive turbine (143) interconnected by a second shaft (127), the first and second core modules (190, 191) being axially spaced.

Abstract: Methods and systems automatically detect, classify and/or mitigate sensor errors using partial qualitative and quantitative knowledge of the subsystems. In various examples, sensor fault detection is performed with a custom designed representation scheme covering causality, correlation, system of equality and inequalities, and an associated logic. The logic is described by a set of algorithmic steps to iteratively assign trustworthiness level of sensors. Sensor fault classification is performed by combining mathematical and statistical techniques that can be utilized to expose bias, drift, multiplicative calibration error, precision degradation and spike error. Sensor fault mitigation is also performed on identified bias, drift, multiplicative calibration error, precision degradation and spike error.

Abstract: A switched reluctance generator and devices and methods for its control are concerned with generators and controls which can operate in an aerospace environment. The generator may have: a rotor having rotor poles; a stator having stator poles; and a controller. Either the rotor or stator poles each have windings to which current can be supplied to energise the poles and from which current can be drawn to a load; and the controller is arranged to: periodically excite each of the windings in turn to a pre-determined level of current; measure the current generated in each winding; cease the excitation when the current generated in each winding exceeds the excitation current; and direct the generated current in each winding to the load. The generator may thereby avoid the need to determine the position of the rotor poles relative to the stator poles to provide the commutation of the generator.

Abstract: The present invention provides a laser welding process and a holding fixture for holding a first and a second body during a laser welding process. A first body and a second body for welding together along at least one weld line to form a joined component are immobilised in the holding fixture by a back clamp and a front clamp of the fixture. A shielding gas is supplied, from respective plenums formed in the back and front clamps, to back and front sides of the component along the weld line. Laser welding the first and second bodies together along the weld line, the laser weld thus-formed penetrating from the front side to the back side of the component.