Abstract: A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.

Abstract: An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side.

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side.

Abstract: A turbofan exhaust system includes at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge-and an outer lateral edge. The upper edge is upstream with respect to the lower edge. The outer lateral edge of the exhaust nozzle is also upstream of the inner lateral edge. This arrangement makes it possible to reduce the noise perceived in the cabin of the aircraft at the same time as the noise perceived on the ground.

Abstract: The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer lateral part (ext), defining a leading edge (115) between an external wall (111) of the nacelle and an internal wall (113) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part (115ext) is to the rear with respect to the leading edge of the inner lateral part (115int). Preferably, the leading edge of the upper part (115S) is likewise to the rear with respect to the leading edge of the lower part (115I).

Abstract: The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary cowl surrounding the primary cowl to define a secondary annular channel, the secondary cowl comprising a stationary portion and a movable portion disposed to extend the stationary portion and capable of moving longitudinally upstream and downstream relative to the stationary portion and relative to the primary cowl so as to vary the exhaust section and/or the throat section of the nozzle, the stationary portion of the secondary cowl presenting a plurality of spaced-apart repetitive patterns disposed extending its trailing edge, and the movable portion of the secondary cowl including in its outside surface a plurality of indentations of shapes complementary to the patterns of the stationary portion.

Abstract: The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary cowl surrounding the primary cowl to define a secondary annular channel, the secondary cowl comprising a stationary portion and a movable portion disposed to extend the stationary portion and capable of moving longitudinally upstream and downstream relative to the stationary portion and relative to the primary cowl so as to vary the exhaust section and/or the throat section of the nozzle, the stationary portion of the secondary cowl presenting a plurality of spaced-apart repetitive patterns disposed extending its trailing edge, and the movable portion of the secondary cowl including in its outside surface a plurality of indentations of shapes complementary to the patterns of the stationary portion.

Abstract: The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer lateral part (ext), defining a leading edge (115) between an external wall (111) of the nacelle and an internal wall (113) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part (115ext) is to the rear with respect to the leading edge of the inner lateral part (115int). Preferably, the leading edge of the upper part (115S) is likewise to the rear with respect to the leading edge of the lower part (115I).

Abstract: The present invention relates to a turbofan exhaust system comprising at least one exhaust nozzle (13; 17) with a trailing edge having an upper edge (13s; 17s), a lower edge (13i; 17i), an inner lateral edge (13int; 17int) and an outer lateral edge (13ext; 17ext), the upper edge (13s; 17s) being upstream with respect to the lower edge (13i; 17i). According to the invention, the exhaust system is characterized in that the outer lateral edge (13ext; 17ext) of the exhaust nozzle is also upstream of the inner lateral edge (13int; 17int). This arrangement makes it possible to reduce the noise perceived in the cabin of the aircraft at the same time as the noise perceived on the ground.