A variable area nozzle assembly (46) for a gas turbine engine includes a fixed structure (48) surrounding an exhaust duct (50) extending along a nozzle centerline (52). The fixed structure (48) includes an upper side and a lower side opposite the upper sid...

A method of controlling a speed of a gas turbine engine (10,110) including a gas generator or high pressure spool (24,124) and a power turbine or low pressure spool (20,120) rotating independently from one another, including controlling a rotational speed ...

An aircraft gas turbine engine (10) has a row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to a fan (31) in the engine's fan section (14). The FLADE fan blades (5) extend across a FLADE duct (3) circumscribing the fan sect...

A nacelle assembly for a high-bypass gas turbine engine is disclosed and includes a variable area fan nozzle (VAFN) (45) including at least one second fan nacelle section (42) movable relative to the first fan nacelle section (40) to modify an area of the ...

A method for operating a gas turbine engine system (1) under baseload and/or a high part load conditions is disclosed, said gas turbine engine system (1) comprising a gas turbine engine (2) with at least one compressor (5) with at least one row of adjustab...