A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.

A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.

A cooling system for an aircraft has at least one moveable member configured to cover an opening formed within an aircraft outer skin. An actuator moves the at least one moveable member between a fully open position where external atmosphere air can be directed through the opening to an internal passage enclosed by the aircraft outer skin and a fully closed position where the opening is covered. A controller selectively controls the actuator to move the at least one moveable member between the fully open and fully closed positions. An aircraft engine and a method of cooling an aircraft engine in an aircraft are also disclosed.

A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.