{
  "$type": "site.standard.document",
  "description": "An aft liner seal (20) for a combustor for a gas turbine includes an inner shell (30) having an inner and outer surface and central axis. The aft liner seal has an outer shell (38) positioned over the inner shell that has an inner and outer surface and central axis coaxial with the inner shell. One…",
  "path": "/patents/1008756",
  "publishedAt": "2011-10-12T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/00",
    "GAS TURBINE EFFICIENCY SWEDEN [SE]"
  ],
  "textContent": "An aft liner seal (20) for a combustor for a gas turbine includes an inner shell (30) having an inner and outer surface and central axis. The aft liner seal has an outer shell (38) positioned over the inner shell that has an inner and outer surface and central axis coaxial with the inner shell. One of the outer surface of the inner shell or the inner surface of the outer shell has grooves (36) angled relative to the central axis. The angled grooves and adjacent portions of the inner surface of the outer shell or the outer surface of the inner shell form cooling passages. The cooling air exits the cooling passages at an exit angle that is matched to a swirl angle of the combustor flow. Matching of the exit angle and the swirl angle minimizes shear of cooling air with respect to flow exiting the combustor liner.",
  "title": "Angled seal cooling system"
}