Rolls-royce Corporation

Lg Fuel Cell Systems Inc.

Philip D Butler

Gerard D Agnew

Chloe J Palmer

Michele Bozzolo

Eric W Dean

Robert Hay Cunningham

Robert D Collins

Malcolm L Hillel

Christopher Clay

Peter McNeely

Gary Saunders

A system for capture of atmospheric carbon dioxide. The system includes a carbon dioxide capture device having a capture medium operable to capture atmospheric carbon dioxide under a first set of thermodynamic conditions, and to release carbon dioxide under a second set of thermodynamic conditions different to the first set of thermodynamic conditions. The first set of thermodynamic conditions includes a first temperature range and the second set of thermodynamic conditions includes a second temperature range. A heat engine is configured receive a working fluid at an inlet temperature and arranged to discharge at least a portion of the working fluid at a discharge temperature in the second temperature range or higher, and a heat transfer arrangement is configured to convey heat from discharged working fluid to the capture medium to release carbon dioxide therefrom.

Carbon dioxide capture

An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.

Aircraft propulsion system

A reformer module () comprises a hollow support member () having at least one passage () extending longitudinally therethrough. The hollow support member () has an external surface (), a barrier layer () arranged on at least a portion of the external surface () of the hollow support member (), a catalyst layer () arranged on the barrier layer () and a sealing layer () arranged on the catalyst layer () and the external surface () of the hollow support member () other than the at least a portion of the external surface of the hollow support member (). By providing the barrier layer () and the catalyst layer () on the exterior surface () of the hollow support member (), the distribution of the barrier layer () and/or the catalyst layer () may be more precisely controlled and thus a non-uniform distribution of barrier layer () and/or catalyst layer () may be achieved.

Reformer module

A gas turbine engine (,) combustion chamber (,) comprises a primary combustion zone (,) and a secondary combustion zone(,) in which lean mixtures of fuel and air are burned. Air is supplied to a first mixing duct (,) through a swirler (,). Air is supplied to an additional mixing duct (,) through a swirler (,) and hydrocarbon fuel is supplied to the additional mixing duct (,) through a swirler (,). The hydrocarbon fuel and air is mixed and reacted in a catalytic partial oxidation reaction zone (,) which produces a product gas comprising a mixture of hydrogen, carbon monoxide, carbon dioxide, water and unreacted hydrocarbon fuel. Additional hydrocarbon fuel is supplied from apertures (,) and is mixed with the product gas in a mixing chamber (,) and this mixture is supplied to the first mixing duct (,) and mixes with the air. The first mixing duct (,) supplies a lean mixture of fuel into the primary combustion zone (,). The arrangement enables the combustion chamber (,) to operate with more stability or at leaner fuel to air ratios.

Combustion chamber and a method of operation thereof

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Derby, United Kingdom

Philip D Butler