Abstract: A powder deposition apparatus has a build plate, a powder source, a recoater arm, and an energy beam. The recoater arm is formed from ferromagnetic material. The recoater arm is arranged to deliver a layer of powder from the powder source across the working surface of the build plate prior to the energy beam fusing a predetermined portion of the delivered powder layer. The recoater arm comprises a magnetic portion.

Abstract: A powder deposition apparatus has a build plate, a powder source, a recoater arm, and an energy beam. The recoater arm is formed from ferromagnetic material. The recoater arm is arranged to deliver a layer of powder from the powder source across the working surface of the build plate prior to the energy beam fusing a predetermined portion of the delivered powder layer. The recoater arm comprises a magnetic portion.

Abstract: An additive layer manufactured component has a first wall portion and a second wall portion with a volume defined between the first and second wall portions. The volume contains unconsolidated powder material. A technique for removing the unconsolidated powder involves saturating the unconsolidated powder material with a dipole fluid, reducing the temperature of the saturated unconsolidated powder material to a temperature below the freezing temperature of the dipole fluid, and then allowing the dipole fluid to freeze. The temperature of the saturated unconsolidated powder material is then raised to a temperature above the melting temperature of the dipole fluid, whereupon the unconsolidated powder material may be removed from the volume.

Abstract: A cooling system is provided for cooling a turbine of a gas turbine engine. The system has first and second flow paths for guiding cooling air received from the compressor of the engine. The routes of both flow paths bypass the combustor of the engine. The system also has a preswirler for receiving the cooling air at the ends of the two flow paths, swirling the cooling air tangentially to the engine axis, and delivering the swirled cooling air to a rotor of the turbine. The first flow path is routed through a heat exchanger which cools the cooling air guided by the first flow path relative to the cooling air guided by the second flow path.

Abstract: A turbine array including: a plurality of turbines; an electrical machine connected to each of the turbines and to an electrical grid; wherein at least one of the electrical machines is a motor-generator which can operate in a motor mode or a generator mode, and wherein the other electrical machines are generators; and a controller for detecting a loss-of-grid event; wherein the controller sets the motor-generator to the motor mode when a loss-of-grid event is detected, the motor-generator being driven by the generators and thereby providing a load to the generators.

Abstract: A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.

Abstract: This invention relates to a generator arrangement, including: a generator located within a flow passage wherein the flow passage has an inlet and an outlet, and the generator includes at least one contra-rotating blade arrangement which is configured to be rotated about a principle axis of the generator by a flow of liquid in the flow passage, and wherein the at least one blade has an adjustable pitch; an array of sensors located downstream of the blade arrangement for detecting the outlet flow conditions; a controller for determining the outlet flow conditions on the basis of conditions sensed by the sensor array; and, a pitch control system for adjusting the pitch of the at least one blade so as to affect the flow conditions at the outlet of the flow passage.

Abstract: A turbine array including: a plurality of turbines; an electrical machine connected to each of the turbines and to an electrical grid; wherein at least one of the electrical machines is a motor-generator which can operate in a motor mode or a generator mode, and wherein the other electrical machines are generators; and a controller for detecting a loss-of-grid event; wherein the controller sets the motor-generator to the motor mode when a loss-of-grid event is detected, the motor-generator being driven by the generators and thereby providing a load to the generators.

Abstract: A cooling system is provided for cooling a turbine of a gas turbine engine. The system has first and second flow paths for guiding cooling air received from the compressor of the engine. The routes of both flow paths bypass the combustor of the engine. The system also has a preswirler for receiving the cooling air at the ends of the two flow paths, swirling the cooling air tangentially to the engine axis, and delivering the swirled cooling air to a rotor of the turbine. The first flow path is routed through a heat exchanger which cools the cooling air guided by the first flow path relative to the cooling air guided by the second flow path.

Abstract: A system for cooling cooling-air in a gas turbine engine, the system having an electricity generating fuel-cell, and an arrangement for receiving water produced by the fuel cell, delivering the water to the engine, and cooling cooling-air inside the engine using the water.

Abstract: A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.