{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "An operating method is provided during which a plurality of start parameters for a gas turbine engine are determined (402). A first of the start parameters is indicative of a temperature of air at an inlet into the gas turbine engine. A second of the start parameters is indicative of a pressure of…",
  "path": "/patents/1397024",
  "publishedAt": "2025-12-17T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C7/26",
    "RTX CORP [US]"
  ],
  "textContent": "An operating method is provided during which a plurality of start parameters for a gas turbine engine are determined (402). A first of the start parameters is indicative of a temperature of air at an inlet into the gas turbine engine. A second of the start parameters is indicative of a pressure of the air at the inlet. Rotation of a rotating assembly of the gas turbine engine (22) is driven (404). The rotating assembly includes a compressor rotor and a turbine rotor. Fuel is directed (408) into a combustion chamber of the gas turbine engine based on the start parameters and a speed parameter. The speed parameter is indicative of a speed of the rotation of the rotating assembly. A mixture of the fuel and compressed air within the combustion chamber is ignited (410) to start the gas turbine engine.",
  "title": "SYSTEMS AND METHODS FOR STARTING A GAS TURBINE ENGINE"
}