Patent ID: 7717369

Claim:
A power plant ( 18 ), comprising: at least one turboshaft engine ( 8 ) for driving a main rotor ( 3 ) of a rotary wing aircraft ( 1 ) via a main gearbox ( 7 ) and a rotor shaft ( 6 ), the engine ( 8 ) being disposed substantially in a longitudinal direction, lying on or parallel with the longitudinal axis X of the aircraft ( 1 ) and behind the main gearbox ( 7 ) relative to the longitudinal direction of axis X, wherein the main gearbox ( 7 ) is driven in rotation by a power transmission shaft ( 10 ) connected to a free turbine ( 11 ) of the engine ( 8 ), the free turbine ( 11 ) is driven in rotation by the gas generator ( 30 ) of the engine ( 8 ), which is fed with air via an air inlet body ( 20 ), the hot gas is exhausted via a nozzle ( 15 ), and said air inlet body ( 20 ) is substantially parallel to the engine ( 8 ) and has a first end ( 21 ) defining an air inlet exposed to ambient atmosphere in front of the hot gas exhaust nozzle ( 15 ), the air inlet being substantially in a transverse Y,Z plane containing the rotor shaft ( 6 ) of the main rotor ( 3 ), and a second end ( 22 ) connected to the engine ( 8 ) at a rearmost zone of the engine ( 8 ) that is rearmost relative to the longitudinal direction X.