{
  "$type": "site.standard.document",
  "description": "The invention relates to a cooling air guidance system in the high-pressure turbine section of a gas turbine engine, wherein a portion of the air flow exiting the compressor section of the engine and guided past the gas turbine combustor is conducted via a first swirl system provided in a partition…",
  "path": "/patents/1111976",
  "publishedAt": "2001-06-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/081",
    "ROLLS ROYCE DEUTSCHLAND [DE]"
  ],
  "textContent": "The invention relates to a cooling air guidance system in the high-pressure turbine section of a gas turbine engine, wherein a portion of the air flow exiting the compressor section of the engine and guided past the gas turbine combustor is conducted via a first swirl system provided in a partition wall into a swirl chamber upstream of the first turbine disk and from there is supplied in particular to the air-cooled blades of this disk for cooling purposes, and wherein a further portion of this air flow can likewise reach the face side of the first turbine disk via a second air transfer system which, viewed in the radial direction, lies further inward than the first swirl system. According to the invention, the second air transfer system is likewise designed as a swirl system opening into the swirl chamber. Preferably, a sealing system is provided between a section of the partition wall bounding the swirl chamber and a turbine shaft section adjacent to this section, which sealing system permits less air leakage than the labyrinth seals customarily provided at this location.",
  "title": "Cooling air path for the rotor of a gas turbine engine"
}