{
  "$type": "site.standard.document",
  "description": "The engine (1) has a turbomachine (2) i.e. gas turbine, comprising a compressor (20), a combustion chamber (23) and a turbine (26). A free piston compressor (3) is coupled with the turbomachine and comprises a compressor piston (30) and a cylinder chamber (31) with a cylinder and a motor piston…",
  "path": "/patents/983236",
  "publishedAt": "2013-10-16T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C5/08",
    "MTU AERO ENGINES AG [DE]"
  ],
  "textContent": "The engine (1) has a turbomachine (2) i.e. gas turbine, comprising a compressor (20), a combustion chamber (23) and a turbine (26). A free piston compressor (3) is coupled with the turbomachine and comprises a compressor piston (30) and a cylinder chamber (31) with a cylinder and a motor piston (32). A part of a fluid i.e. air, conveyed through the compressor piston is supplied to the cylinder, and another part of the fluid is provided for tempering i.e. cooling, the combustion chamber and/or the turbine. An intercooler (50) is arranged between the compressor and the free piston compressor. Independent claims are also included for the following: (1) an aircraft engine (2) a method for operating a turbomachine (3) a method for increasing thrust of an aircraft engine.",
  "title": "Thermal engine for free piston compressor"
}