{
  "$type": "site.standard.document",
  "description": "A system for stabilizing combustion in a gas turbine engine comprises a) optical sensing means embedded within a fuel injector for observing conditions within a combustion chamber of a gas turbine engine; b) means for detecting combustion instabilities based upon conditions observed by the optical…",
  "path": "/patents/997520",
  "publishedAt": "2012-10-10T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/02",
    "ROSEMOUNT AEROSPACE INC [US]"
  ],
  "textContent": "A system for stabilizing combustion in a gas turbine engine comprises a) optical sensing means embedded within a fuel injector for observing conditions within a combustion chamber of a gas turbine engine; b) means for detecting combustion instabilities based upon conditions observed by the optical sensing means; and c) means for modulating a fuel flow rate to reduce detected combustion instabilities.",
  "title": "System for observing combustion conditions in a gas turbine"
}