Abstract: A combustor assembly (16) for a gas turbine having an annular combustor body and an annular combustor rear. The combustor body and the combustor rear are connected by: i) fit between a radially outer surface of the radially outer wall of the combustor rear and a radially inner surface of the radially outer wall of the combustor body, ii) fit between a radially inner surface of the radially inner wall of the combustor rear and a radially outer surface of the radially inner wall of the combustor body, and iii) one or more retention pins extending radially through respective apertures in the combustor body and in the combustor rear. The combustor rear tapers towards the engine axis as it extends rearwardly.

Abstract: A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.

Abstract: A gas turbine engine includes a bypass duct, an inlet cowl, and a heat-exchanger assembly. The bypass duct is configured to direct air through a flow path to provide thrust to propel the gas turbine engine. The inlet cowl is located in the bypass duct and configured to collect a portion of the air flowing in the bypass duct. The heat-exchanger assembly is removably coupled with the inlet cowl and configured to receive the portion of the air from the inlet cowl.

Abstract: There is disclosed a method of providing through-thickness reinforcement in a laminated material. A guide foot is moved to a datum location relative the laminated material, at which the guide foot abuts a reinforcement zone on a surface of the laminated material. An insertion operation is conducted by inserting an insertion element through the guide foot into the laminated material along an insertion direction when the guide foot is in the datum location. The insertion element comprises a needle for forming a hole in the laminated material; a reinforcement rod to be received in the laminated material; or a tamping pin for tamping a reinforcement rod received in the laminated material. A corresponding insertion apparatus is disclosed.

Abstract: A fluid storage tank can be configured to store a cooling fluid in a liquid state and a gas state. A first heat exchanger can be configured to release heat into the fluid storage tank. A second heat exchanger can be disposed fluidly downstream of the fluid storage tank and configured to exchange heat between the cooling fluid and a heat load. A pressure control device can be disposed fluidly downstream of the second heat exchanger. One of the first cooling fluid that has been heated by the second heat exchanger or a second cooling fluid different than the first cooling fluid can pass through the first heat exchanger and thereby heat upstream first cooling fluid resident in the fluid storage tank.

Abstract: A section of a continuum arm robot including a pair of pivot points at a first and second end of the joint, the section further having a first and second connecting rod connected to the section and joining at the centre of the section, the connecting rods has a plurality of gear teeth at the peripheral ends of the connecting rod that intermesh at a central point on the section.

Abstract: Synchronisation methods for synchronising processor nodes of an Engine Control and Monitoring System (ECaMS) for an engine. A method comprises counting, at a first acquisition integrated circuit in a first processor node of the ECaMS, a first control cycle count, and storing at the first acquisition integrated circuit a first transmission slot index. The method further comprises counting a second control cycle count and storing a second transmission slot index at a second acquisition integrated circuit in a second processor node of the ECaMS. The method also comprises transmitting a message including the first control cycle count and transmission slot index from the first to second acquisition integrated circuits, and receiving the message at the second acquisition circuit. The method also comprises synchronising the first and second processor nodes using the first and second control cycle counts and transmission slot indexes.

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: Engine Control and Monitoring Systems (ECaMS) for engines are disclosed. An ECaMS comprises a first processor node and a second processor node. The first processor node comprises a first acquisition integrated circuit (IC), a first output IC, and a first processor. The second processor node comprises a second acquisition IC, a second output IC, and a second processor. The first acquisition IC is connected directly to the second acquisition IC.

Abstract: A system for coupling at least one component to a blade of a gas turbine engine includes a blade holder and an intensifier tool. The intensifier tool includes a plate configured to contact the component and a heating device coupled to the plate. The system further includes an adhesive layer disposed between the component and the blade, a pressure strip coupled to the plate and the blade that fully encloses the plate, and a pressure applicator coupled to the plate. The adhesive layer has a uniform bond thickness along a length of the component due to pressure applied by the pressure applicator. Upon being heated by the heating device, the adhesive layer is cured, thereby coupling the component to the blade.

Abstract: Methods for modifying an Engine Control and Monitoring System (ECaMS) for an engine. A method comprises identifying a provisioning deficit in the ECaMS, wherein the ECaMS comprises a first processor node and a second processor node. The first processor node comprises a first acquisition integrated circuit (IC), a first output IC, and a first processor. The second processor node comprises a second acquisition IC, a second output IC, and a second processor. The first acquisition IC is connected directly to the second acquisition IC. The method comprises connecting an expansion unit to the ECaMS. The expansion unit comprises one or more expansion unit ICs, said one or more expansion unit ICs being connected to one or more ICs of the ECaMS.

Abstract: A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

Abstract: An apparatus for manufacturing an annular or semi-annular composite component having a circumferentially-extending base and a flange, the apparatus including: a loom for weaving a woven preform of fibre reinforcement material for the composite component; a rotatable mandrel configured to receive and draw the woven preform through the loom for weaving; and a guide disposed between the loom and the rotatable mandrel, configured so that a woven preform drawn by the rotatable mandrel along a guide path under tension engages the guide to transition to a flanged profile at a lip of the guide before being received on the mandrel.

Abstract: A gas turbine engine includes an engine core including a compressor, a combustor, and a turbine, the compressor being connected to the turbines through a respective shaft; and a cabin blower system comprising: an electric variator comprising a first electrical machine connected to a first shaft arranged along a first axis, a second electrical machine connected to a second shaft arranged along a second axis, and a power management system; a cabin blower comprising a compressor driven by a third shaft arranged along a third axis, the compressor comprising an air inlet and an air outlet; and a differential gearbox. The gas turbine engine further includes an accessory gearbox arranged within an accessory gearbox casing and adapted to drive the cabin blower system.

Abstract: A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.

Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.

Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Abstract: A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.

Abstract: A vortex particle separator adapted for use with a gas turbine engine includes a vortex tube, a plurality of swirl vanes, and an outlet tube. The vortex tube receives atmospheric air laden with particles. The plurality of swirl vanes are arranged within the vortex tube and separate the atmospheric air into a first flow of air having the particles and a second flow of air that is relatively free of the particles. The outlet tube extends into the vortex tube to define a scavenge passageway between the outlet tube and the vortex tube that receives the first flow of air. The outlet tube defines an intake passageway that receives the second flow of air. The vortex particle separator further includes a layer of material having a low coefficient of restitution on at least one of an interior surface of the vortex tube and a surface of the swirl vanes.

Abstract: A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.