{
  "$type": "site.standard.document",
  "description": "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…",
  "path": "/patents/1410061",
  "publishedAt": "2025-01-01T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "C01B3/047",
    "RTX CORP [US]"
  ],
  "textContent": "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).",
  "title": "ENGINE USING CRACKED AMMONIA FUEL"
}