{
  "$type": "site.standard.document",
  "coverImage": {
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  "description": "A stator vane for a gas turbine engine section includes a stator vane (120) having an airfoil (122, 140) extending between a leading edge (124, 146) and a trailing edge (138, 152). The airfoil (132, 140) has a suction side (126, 144) and a pressure side (128, 142). There is at least one…",
  "path": "/patents/1433210",
  "publishedAt": "2022-08-31T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D17/162",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A stator vane for a gas turbine engine section includes a stator vane (120) having an airfoil (122, 140) extending between a leading edge (124, 146) and a trailing edge (138, 152). The airfoil (132, 140) has a suction side (126, 144) and a pressure side (128, 142). There is at least one piezoelectric actuator (130, 134, 148, 150) for changing a shape of at least one of the leading edge (124, 146) and the trailing edge (138, 152). A gas turbine engine (20) is also disclosed.",
  "title": "GAS TURBINE ENGINE WITH MORPHING VARIABLE COMPRESSOR VANES"
}