{
  "$type": "site.standard.document",
  "description": "A component for a gas turbine engine (20) includes a mateface (82) with a purge flow interface (98), the mateface (82) comprises a pocket (100) located in communication with a feather seal slot (90) in the mateface (82). A vane (72) for a gas turbine engine (20) includes a platform (76, 78) that…",
  "path": "/patents/1416151",
  "publishedAt": "2023-10-25T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/005",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A component for a gas turbine engine (20) includes a mateface (82) with a purge flow interface (98), the mateface (82) comprises a pocket (100) located in communication with a feather seal slot (90) in the mateface (82). A vane (72) for a gas turbine engine (20) includes a platform (76, 78) that extends from the airfoil (74), the platform (76, 78) comprising a mateface (82) with a feather seal slot (90) and a pocket (100) in communication with the feather seal slot (90), wherein the pocket (100) is of a cross-sectional shape larger than the feather seal slot (90).",
  "title": "VANE FOR A GAS TURBINE ENGINE AND METHOD FOR COMMUNICATING A COOLING AIRFLOW WITHIN A COMPONENT"
}