{
  "$type": "site.standard.document",
  "description": "A fuel nozzle (70) for a gas turbine (10) generally includes a main body (72) having an upstream end (78) axially separated from a downstream end (80). The main body at least partially defines a fuel supply passage (86) that extends through the upstream end and at least partially through the main…",
  "path": "/patents/973824",
  "publishedAt": "2014-06-11T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/222",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "A fuel nozzle (70) for a gas turbine (10) generally includes a main body (72) having an upstream end (78) axially separated from a downstream end (80). The main body at least partially defines a fuel supply passage (86) that extends through the upstream end and at least partially through the main body. A fuel distribution manifold (74) is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages (92) that extend through the fuel distribution manifold. A plurality of fuel injection ports (96) defines a flow path (98) between the fuel supply passage and each of the plurality of axially extending passages.",
  "title": "A fuel nozzle for a combustor of a gas turbine engine"
}