{
  "$type": "site.standard.document",
  "description": "An aircraft powerplant (20) assembly includes a compressor section (36), a combustor section (37), a turbine section (38), a flowpath and a rotating structure (70). The flowpath extends through the compressor section (36), the combustor section (37) and the turbine section (38). The rotating…",
  "path": "/patents/965110",
  "publishedAt": "2026-05-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/027",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "An aircraft powerplant (20) assembly includes a compressor section (36), a combustor section (37), a turbine section (38), a flowpath and a rotating structure (70). The flowpath extends through the compressor section (36), the combustor section (37) and the turbine section (38). The rotating structure (70) includes a balancing device (76) and a bladed rotor disposed in the turbine section (38) or the compressor section (36). The balancing device (76) is configured to rotationally balance the rotating structure (70) about a rotational axis (72) of the rotating structure (70). The balancing device (76) includes a mounting platform (108) and a plurality of balancing masses (88). The mounting platform (108) includes a plurality of mounting apertures (120). The balancing masses (88) are arranged circumferentially about the axis (72). Each of the balancing masses (88) includes a shank (130) and a head (128). The shank (130) of each of the balancing masses (88) is threaded into a respective one of the mounting apertures (120). The head (128) of each of the balancing masses (88) is disposed radially inboard of the mounting platform (108).",
  "title": "ASSEMBLIES FOR AN AIRCRAFT POWERPLANT AND METHOD FOR BALANCING A ROTATING STRUCTURE OF A GAS TURBINE ENGINE"
}