An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.

A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.