{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) including a temperature sensor assembly (110) that continuously monitors an operating temperature within a multi-stage rotor assembly (18) of the turbine engine is described. A plurality of cavities (100) are defined within the multi-stage rotor assembly. The temperature…",
  "path": "/patents/1101891",
  "publishedAt": "2002-09-11T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/085",
    "GEN ELECTRIC [US]"
  ],
  "textContent": "A gas turbine engine (10) including a temperature sensor assembly (110) that continuously monitors an operating temperature within a multi-stage rotor assembly (18) of the turbine engine is described. A plurality of cavities (100) are defined within the multi-stage rotor assembly. The temperature sensor assembly includes a plurality of temperature sensor assemblies that monitor the temperature within each of the rotor assembly cavities. Each temperature sensor assembly includes a plurality of support guide tubes (140,142) attached to the engine and extending from an outer casing (72) of the engine to each cavity. A temperature sensor (121) is inserted through the guide tubes and positioned within each cavity.",
  "title": "Methods and apparatus for operating gas turbine engines"
}