{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (10) includes a fan section (12), a compressor section (14), and a turbine section (18). The fan section (12) has a plurality of vane assemblies (64) spaced circumferentially about an engine axis (A) and each including an airfoil (66) extending between a leading edge (66a) and…",
  "path": "/patents/1402362",
  "publishedAt": "2026-01-21T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/162",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (10) includes a fan section (12), a compressor section (14), and a turbine section (18). The fan section (12) has a plurality of vane assemblies (64) spaced circumferentially about an engine axis (A) and each including an airfoil (66) extending between a leading edge (66a) and a trailing edge (66b), a control rod (68) extending through the airfoil (66), and a mechanism driven by the control rod (68) to change the shape of the airfoil (66).",
  "title": "MORPHING STRUCTURES FOR ADJUSTABLE FAN INLET GUIDE VANES"
}