CRACKING AND SEPARATION OF AMMONIA FUEL

A gas turbine engine includes a cracking device (74) that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device (76) that separates hydrogen downstream of the cracking device (74), wherein residual ammonia and nitrogen a...

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Bibliographische Detailangaben
Hauptverfasser:	COCKS, Peter, SMITH, Lance L
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes a cracking device (74) that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device (76) that separates hydrogen downstream of the cracking device (74), wherein residual ammonia and nitrogen are exhausted as a residual flow (82). The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow (80). A combustor (46) is configured to receive and combust the hydrogen flow (80) from the separation device to generate a gas flow (58). A compressor section (44) is configured to supply compressed air to the combustor (46). A turbine section (48) is in flow communication with the gas flow (58) produced by the combustor (46) and is mechanically coupled to drive the compressor section (44).