{
  "$type": "site.standard.document",
  "description": "A gas turbine engine support system (60) includes a support arc segment piece (62) that defines radially inner and outer sides (62a, 62b), axially forward and aft sides (62c, 62d), and first and second circumferential mate face sides (62e, 62f). The radially inner side (62a) has a radially open…",
  "path": "/patents/1417271",
  "publishedAt": "2024-02-21T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/246",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine support system (60) includes a support arc segment piece (62) that defines radially inner and outer sides (62a, 62b), axially forward and aft sides (62c, 62d), and first and second circumferential mate face sides (62e, 62f). The radially inner side (62a) has a radially open socket (64) that is configured to engage a mating component (70) and transmit loads from the mating component (70). The radially open socket (64) is elongated in an axial direction with respect to the axially forward and aft sides (62c, 62d). The support arc segment piece (62) has radial and axial reaction surfaces (66a, 66b) that are configured, respectively, to transmit radial and axial components of the loads from the mating component (70).",
  "title": "VANE SUPPORT SYSTEM"
}