{
  "$type": "site.standard.document",
  "description": "A section (100) for a gas turbine engine (20) includes a rotating structure, a stationary structure (89), and a flow guide assembly (78, 178, 278, 378) arranged generally between the rotating structure and the stationary structure (89). A flow path (80) is defined between the flow guide assembly…",
  "path": "/patents/1403224",
  "publishedAt": "2024-11-13T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/001",
    "RTX CORP [US]"
  ],
  "textContent": "A section (100) for a gas turbine engine (20) includes a rotating structure, a stationary structure (89), and a flow guide assembly (78, 178, 278, 378) arranged generally between the rotating structure and the stationary structure (89). A flow path (80) is defined between the flow guide assembly (78, 178, 278, 378) and one of the rotating structure and the stationary structure (89). The flow guide assembly (78, 178, 278, 378) includes a plurality of apertures (82, 182, 282, 382) configured to disrupt acoustic waves of air in the flow path (80). A seal (76) is configured to establish a sealing relationship between the rotating structure and the stationary structure (89), and wherein an inlet (80a) to the flow path (80) is adjacent the seal (76). A gas turbine engine (20) and a method of disrupting acoustic waves in a flow path (80) of a gas turbine engine (20) are also disclosed.",
  "title": "GAS TURBINE ENGINE COMPONENT FOR ACOUSTIC ATTENUATION"
}