{
  "$type": "site.standard.document",
  "description": "A multi-engine system (42) for an aircraft, has: a first engine (10A) having a first output shaft (32), a first core shaft (34), and a first electric machine (51A) operable as a generator drivingly engaged by the first output shaft (32) or the first core shaft (34); a second engine (10B) having a…",
  "path": "/patents/1402706",
  "publishedAt": "2025-03-12T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64C27/12",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A multi-engine system (42) for an aircraft, has: a first engine (10A) having a first output shaft (32), a first core shaft (34), and a first electric machine (51A) operable as a generator drivingly engaged by the first output shaft (32) or the first core shaft (34); a second engine (10B) having a second output shaft (32), a second core shaft (34), and a second electric machine (51B) operable as an electric motor drivingly engaged to the second core shaft (34); a reduction gearbox (46) drivingly engaged by the first output shaft (32) and by the second output shaft (32) for driving a common load (44); and a transmission path between the first engine (10A) and the second engine (10B), the transmission path being independent from the reduction gearbox (46) and being one or more of: a torque-transfer connection between the second core shaft (34) and the first core shaft (34) or the first output shaft (32) via a coupling gearbox (52), and an electrical connection between the generator (51A) and the electric motor to transmit electrical power to the electric motor.",
  "title": "MULTI-ENGINE SYSTEM AND POWER TRANSFER BETWEEN ENGINES THEREOF"
}