A method for assembling a gas turbine engine (10) that includes providing a low-pressure turbine inner rotor (42) configured to rotate in a first direction, providing a low-pressure turbine outer rotor (38) configured to rotate in a second direction that i...

A method of assembling a gas turbine engine (10) that includes rotatably coupling a first low-pressure turbine rotor (106) to a high-pressure turbine (100), rotatably coupling a second low pressure turbine rotor (108) to the first low-pressure turbine roto...

A method for assembling a gas turbine engine includes providing a first fan assembly (12) including a plurality of rotor blades (19) that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan ...

The system (1) comprises a stationary structure, and a rotor structure (3), supported by the stationary structure in such a way that it can rotate about an axis (4) by means of contactless suspension devices, and comprising a central hub (5) to which is co...

Methods and apparatus for assembling a gas turbine engine are provided. The method includes coupling a first turbine shaft that includes m rows of turbine blades within the gas turbine such that the first turbine shaft is rotatable in a first direction, an...

The assembly has a low pressure turbine with a flowpath and located aft of a high pressure spool (33). The low pressure turbine has counter rotatable low pressure inner and outer rotatable turbines. A single direction rotation booster has a row of booster ...

Turbojet engine comprising a compressor (1), a combustion chamber (2), and at least one turbine (6) receiving the combustion gases, characterized in that it comprises a precombustion chamber (3) comprising means for supplying an oxidizer and a fuel (4,5), ...