Rolls-royce Corporation

Adam P Chir

Andrew Martin Rolt

Richard Edward Mellor

Gregory Collecutt

Richard Mellor

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.

Powder deposition apparatus and a method of using the same

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.

Turbine cooling system

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.

Turbine array and a method of controlling a turbine array during a loss-of-grid event

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.

Cooling system for an aero gas turbine engine

A bidirectional water turbine including: an upstream rotor and a downstream rotor, wherein the upstream rotor and downstream rotor are contra-rotating and each rotor includes a plurality of blade, the blades of the upstream and downstream rotors having substantially the same profile.

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Derby, United Kingdom

Adam P Chir