Abstract: A cooling ring for a combustor system having an inner wall, an outer wall spaced apart from the inner wall, and a discharge nozzle disposed downstream of the inner wall includes an upstream portion disposed adjacent to the outer wall, a downstream portion spaced apart from the upstream portion, and a middle portion connecting the upstream portion to the downstream portion. The middle portion includes a plurality of first apertures and a plurality of second apertures. Each first aperture extends from a first inner surface portion to an outer surface portion of the middle portion along a first aperture axis and is configured to supply a cooling fluid to a cavity. Each second aperture extends from the second inner surface portion to the outer surface portion along a second aperture axis and is configured to supply the cooling fluid to the discharge nozzles.

Abstract: Described herein is a non-contact excitation system for a spin rig comprising: a plurality of test piece elements for attachment to a test piece for rotation about an axis of rotation of the spin rig; and a plurality of exciter elements arranged around the axis of rotation, wherein the test piece elements and the exciter elements are magnetically attractive; wherein the test piece elements and/or the exciter elements comprise magnets; and wherein, in use, the exciter elements are arranged around the test piece; wherein each exciter element is axially and radially offset from the plurality of test piece elements. Also described is a method of testing a test piece using the system.

Abstract: A gas turbine engine for an aircraft includes 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, and a gearbox. The turbine is the lowest pressure turbine of the engine, and has a turbine length that is the distance between the root of the most upstream blade of the turbine at its leading edge and the root of the most downstream blade of the lowest pressure turbine at its trailing edge. The engine core further includes three bearings arranged to support the core shaft. The three bearings include a forward bearing and two rearward bearings, with a minor span being defined as the axial distance between the two rearward bearings. A ratio of the minor span to a turbine length is equal to or less than 1.05.

Abstract: A filter inductor for a power generation convertor; the filter inductor comprising a toroidal connector and a conductive winding having a first connector and a second connector positioned at each end of the winding, and wherein the conductive winding being formed from at least first and second winding segments which are connected to each other so as to form a continuous winding around the toroidal connector that extends form the first connector to the second connector.

Abstract: A system for wet treatment of at least one component has a chamber configured to receive and at least partially enclose the at least one component. The system also has at least one component support, a plurality of tanks configured to store a corresponding plurality of fluids, at least one nozzle selectively fluidly coupled to the plurality of tanks and configured to spray a fluid towards the at least one component, at least one delivery valve for selectively fluidly coupling the at least one nozzle to the plurality of tanks, at least one port configured to collect the fluid sprayed by the at least one nozzle, and at least one recovery valve for selectively fluidly coupling the at least one port to the plurality of tanks.

Abstract: A method for manufacturing a composite component includes providing a tool switchable between a deposition configuration and a flange-forming configuration. The tool includes a first portion including a first deposition surface, a second portion including a second deposition surface and a pre-form support surface, and a flange-forming block including a curved surface. The method further includes depositing a composite material at least partially on each of the first deposition surface and the second deposition surface in the deposition configuration to provide a composite pre-form. The method further includes moving the second portion relative to the first portion to transition the tool to the flange-forming configuration, which causes the composite pre-form to at least partially engage each of the pre-form support surface and the curved surface. The curved surface defines a radius of a flange of the composite component.

Abstract: A nosecone for a ducted fan gas turbine engine is shown. The nosecone includes a body with an outer surface that tapers in axial extent from an apex to a base of the body, the apex defining a position of 0 percent axial extent and the base defining a position of 100 percent axial extent, and in which the outer surface includes a plurality of undulations extending between a first location on the outer surface and a second location on the outer surface, wherein the first location is positioned at from 0 to 50 percent of axial extent and the second location is positioned at from 85 to 100 percent of axial extent.

Abstract: A method of operating a gas turbine engine, the gas turbine engine including an engine core comprising a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system arranged to supply oil to lubricate the main gearbox; and a heat exchange system arranged to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes controlling the heat exchange system so as to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.

Abstract: A system for controlling a continuum robot whilst inspecting or repairing a component includes a tendon of the continuum robot, a first sensor that generates an information related to a curvature of the first sensor, and at least one actuator that controls at least a pitch angle and/or a radius of the tendon and/or the first sensor. The system has a controller that receives, from the first sensor, the information related to the curvature of the first sensor and corrects a current position of the continuum robot based on the curvature of the first sensor.

Abstract: A cleaning tool for cleaning a component located within a gas turbine engine is disclosed. The cleaning tool includes a tubular body including: a first open end and a second closed end; an engagement portion that is proximal to the second closed end and configured to engage with a support within the gas turbine engine; a nozzle aperture disposed between the first open end and the engagement portion; and a flow channel extending from the first open end and in fluid communication with the nozzle aperture. The flow channel is configured to transport a cleaning fluid from the first open end to the nozzle aperture. The cleaning fluid is delivered to the component through the nozzle aperture. The tubular body is configured to be inserted through a first port of the gas turbine engine from the second closed end, such that the engagement portion engages with the support.

Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

Abstract: A fuel cell system for propulsion of an aircraft or UAV comprises a fuel cell stack comprising at least one fuel cell and a piston compressor arranged to compress air provided to an input thereof and provide resulting compressed air from an output thereof to the cathode input of the fuel cell stack. The piston compressor, which is a positive displacement compressor, reduces the power required for air compression for a given target pressure rise compared to a dynamic or open-flow compressor, such as an axial, centrifugal or mixed-flow compressor, providing improved performance at altitude, and allowing fuel cell-based aircraft and UAV propulsion at very high altitudes up to 30 km, which has previously not been possible.

Abstract: A gas turbine engine for an aircraft includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The fuel spray nozzles include a first and a second subset of fuel spray nozzles. The combustor is operable in a condition in which each of first subset is supplied with fuel at a greater fuel flow rate than each of the second subset. A ratio of nozzles in the first subset to nozzles in the second subset is 1:3 to 1:6. A first idle-MTO nvPM emissions index ratio is EI idle EI max ? TO . EIidle is the nvPM emissions index of the gas turbine engine operating at around 7% available thrust. EImaxTO is the nvPM emissions index of the gas turbine engine operating at around 100% available thrust. The first idle-MTO nvPM emissions index ratio is less than 3.

Abstract: A fuel delivery system for a gas turbine engine comprises a fuel delivery line for connection between a fuel tank and a combustor of the gas turbine engine and configured to deliver a gaseous fuel in use. The fuel delivery system further includes a fuel vent line arranged to connect combustor and fuel delivery line to a fuel vent outlet. The fuel delivery line comprises a fuel delivery valve, the fuel vent line comprises a fuel vent valve, and a flame arrestor is provided between the combustor and the fuel vent outlet.

Abstract: An aircraft propulsion system comprises a core gas turbine engine (201) comprising a core compressor (202, 204) configured to provide core air to a core combustor (206) and a core turbine (208, 209) in fluid flow series. An auxiliary compressor (220) is provided, which is separate to the core compressor (202, 204), and configured to provide air to an auxiliary air system (218). A heat exchanger (218) is provided, which is configured to transfer heat from air from the auxiliary compressor (220) to fuel in the main fuel conduit (217) prior to provision to the core combustor (206).

Abstract: A continuum arm robot segment that has a proximal end section and a distal end section. The continuum arm robot segment has at least one vertebra between the proximal end section and the distal end section, the vertebra being linked to the proximal end section and to the distal end section by linkages, wherein the proximal end section, the distal end section and the at least one vertebra are configured to have hollow cores to provide a passage within the continuum arm robot segment. The continuum arm robot segment also has at least two tendons that are connected to the distal end section and pass through the at least one vertebra and the proximal end section. The at least two tendons are routed helically so that they undergo substantially at least a 360° rotation between the proximal end section and the distal end section.

Abstract: An electrical power system 10 and a method 300 of controlling an electrical power system 10 are provided. The electrical power system 10 comprises a DC:DC power converter 100 connected between a DC power source 11 and a DC electrical network 12. The DC electrical network 12 comprises at least a first zone Z1 for powering a first group of one or more electrical loads 12La-b, a second zone Z2 for powering a second group of one or more electrical loads 12Lc-d, a first controllable circuit breaker X1, and a second controllable circuit breaker X2.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes a body segment and a damping segment that extends along a curvilinear path.

Abstract: There is disclosed a fixing apparatus (10) for fixing a secondary component (14) to a fan blade, the fixing apparatus comprising: a first clamp part (16) comprising a first inner surface (20) and a second clamp part (18) comprising a second inner surface (22), the first inner surface and the second inner surface having a profile corresponding to a profile of a portion of the fan blade (102). The first clamp part and/or the second clamp part comprises a recess (24) in the respective first inner surface and/or second inner surface for receiving the secondary component, and a corresponding heater (28, 30) for applying heat to the secondary component located in the recess in use. The first clamp part and the second clamp part are configured to cooperate with one another to clamp the portion of a blade between them in a clamping operation and to hold the secondary component against the blade when the secondary component is received within the recess.

Abstract: An electrical power system includes: an electrical power source; power converter connected, at an input side, to the electrical power source and including first and second DC output terminals and a capacitor connected between the output terminals; a DC electrical network having first and second input terminals; a resistor; and switch arrangement including several switches. The switch arrangement has: a first configuration in which the resistor is connected in series between the first output terminal of the power converter and the first input terminal of the DC electrical network; a second configuration in which the first output terminal of the power converter is connected to the first input terminal of the DC electrical network bypassing the resistor; and a third configuration in which the resistor is connected in parallel across the capacitor. The electrical power system further includes a control system for controlling a configuration of the switch arrangement.