{
  "$type": "site.standard.document",
  "description": "The turbomachine (1) has a continuous detonation wave engine (6) provided with an annular detonation chamber (7), and a fuel injection system (8) and a priming unit (9) for continuous production of hot gas (F3) from a detonation mixture of fuel and air. A turbine (5) is rotatably driven by the hot…",
  "path": "/patents/995896",
  "publishedAt": "2012-11-21T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/14",
    "MBDA FRANCE [FR]"
  ],
  "textContent": "The turbomachine (1) has a continuous detonation wave engine (6) provided with an annular detonation chamber (7), and a fuel injection system (8) and a priming unit (9) for continuous production of hot gas (F3) from a detonation mixture of fuel and air. A turbine (5) is rotatably driven by the hot gas, and drives a compressor (3). An ejector/mixer system (10) mixes the gas from the chamber with air flow (F2) before directing the gas toward the turbine. The chamber is arranged with another detonation chamber in a concentric manner relative to an axis (2) of the turbomachine.",
  "title": "Turbomachine with detonation chamber and aircraft provided with such a turbomachine"
}