{
  "$type": "site.standard.document",
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  "description": "An embodiment of a combustor for a gas turbine engine includes a combustor case (20), a combustor liner (24) disposed within the combustor case, a fuel nozzle (27), and a torch igniter (10) within the combustor case. The torch igniter (10) includes a combustion chamber (22), a cap (18) defining the…",
  "path": "/patents/1409237",
  "publishedAt": "2024-02-14T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/22",
    "COLLINS ENGINE NOZZLES INC [US]"
  ],
  "textContent": "An embodiment of a combustor for a gas turbine engine includes a combustor case (20), a combustor liner (24) disposed within the combustor case, a fuel nozzle (27), and a torch igniter (10) within the combustor case. The torch igniter (10) includes a combustion chamber (22), a cap (18) defining the upstream end of the combustion chamber, a tip (14) defining the downstream end of the combustion chamber, an annular igniter wall (32) extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall (36) coaxial with and surrounding the igniter wall, and an outlet passage (34) within the tip that fluidly connects the combustion chamber to the combustor. The tip (14) is mounted through the combustor liner, the cap (18) is downstream of the tip, and the torch igniter (10) is downstream of the fuel nozzle and disposed radially between the combustor liner and the combustor case.",
  "title": "GAS TURBINE ENGINE COMBUSTOR WITH AXIALLY ORIENTED INTERNALLY MOUNTED CONTINUOUS IGNITION DEVICE WITH REVERSE FLOW AXIAL ORIENTATION"
}