{
  "$type": "site.standard.document",
  "description": "An airfoil (60) includes an airfoil wall (62) that defines a leading end (62a), a trailing end (62b), a first side (62c), and a second side (62d). Radially-extending ribs (64) partition the interior cavity of the airfoil into first and second cooling channels (72) and a radial cooling passage that…",
  "path": "/patents/1421861",
  "publishedAt": "2025-01-01T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/187",
    "RTX CORP [US]"
  ],
  "textContent": "An airfoil (60) includes an airfoil wall (62) that defines a leading end (62a), a trailing end (62b), a first side (62c), and a second side (62d). Radially-extending ribs (64) partition the interior cavity of the airfoil into first and second cooling channels (72) and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs (80, 82) such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.",
  "title": "AIRFOIL FOR A GAS TURBINE ENGINE HAVING A TURN CHANNEL WITH SPLIT AND FLOW-THROUGH"
}