CRACKING AND SEPARATION OF AMMONIA FUEL

A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as...

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Bibliographische Detailangaben
Hauptverfasser:	Smith, Lance, Cocks, Peter
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CHEMISTRY COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES COMPOUNDS THEREOF CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INORGANIC CHEMISTRY LIGHTING MECHANICAL ENGINEERING METALLURGY NON-METALLIC ELEMENTS WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.