{
  "$type": "site.standard.document",
  "description": "A gas turbine main engine (1) powered by a fuel is disclosed. It comprises a combustion chamber (2) configured to receive fuel through at least one injector (2.1), and a turbopump (3) comprising a pump (3.1), an inlet (3.4) for introducing the fuel in a first state into the pump (3.1), a turbine…",
  "path": "/patents/1399666",
  "publishedAt": "2025-08-27T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C3/22",
    "AIRBUS OPERATIONS SLU [ES]"
  ],
  "textContent": "A gas turbine main engine (1) powered by a fuel is disclosed. It comprises a combustion chamber (2) configured to receive fuel through at least one injector (2.1), and a turbopump (3) comprising a pump (3.1), an inlet (3.4) for introducing the fuel in a first state into the pump (3.1), a turbine (3.2), an outlet (3.5) for discharging the fuel in a second state from the turbine (3.2), the outlet (3.5) being fluidically connected to the combustion chamber (2) through the injector (2.1), and a clutch (3.3) further comprising a shaft (3.3.1). The engine (1) also comprises a heat exchanger (4) comprising an inlet (4.1), fluidically connected to the pump (3.1) of the turbopump (3), and an outlet (4.2), fluidically connected to the turbine (3.2) of the turbopump (3), the heat exchanger (4) being configured for heating fuel in the first state, preferably liquid fuel (LF), from the pump (3.1) into fuel in the second state, preferably conditioned fuel (CF) for the turbine (3.2). The engine (1) further comprises a bypass system (5) fluidically connected with the outlet (4.2) of the heat exchanger (4) and the outlet (3.5) of the turbopump (3), and the shaft (3.3.1) of the clutch (3.3) is coupled both to a main engine accessory gearbox and to a shaft of the turbopump (3). Also disclosed is a method for providing fuel in a second state to the gas turbine main engine (1).",
  "title": "GAS TURBINE"
}