ENGINE USING CRACKED AMMONIA FUEL

A gas turbine engine includes a cracking device (70) that is configured to decompose a portion of an ammonia flow into a flow of component parts of the ammonia flow, a thermal transfer device that is configured to heat the ammonia flow to a temperature above 500 °C (932 °F), a combustor (46) that is configured to receive and combust the flow of component parts of the ammonia flow to generate a high energy gas flow (64), a compressor section (44) that is configured to supply compressed air to the combustor (46), and a turbine section (48) in flow communication with the high energy gas flow (64) produced by the combustor (46) and mechanically coupled to drive the compressor section (44).