Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.

Abstract: Bypass turbine engine, comprising a gas generator surrounded by a nacelle and connected to the latter by tubular arms, a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator, and a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle, the second and third casings being connected together by at least some of the tubular arms, characterized in that it comprises at least one lubricant tank located in the annular space that extends between the first and second casings, and lubricant supply means of the tank or of each tank that comprise at least one supply line extending from the or each tank to at least one filler opening located at the level of the third casing, passing within at least one of said arms connecting the second and third casings.

Abstract: Bypass turbine engine, comprising a gas generator surrounded by a nacelle and connected to the latter by tubular arms, a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator, and a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle, the second and third casings being connected together by at least some of the tubular arms, characterized in that it comprises at least one lubricant tank located in the annular space that extends between the first and second casings, and lubricant supply means of the tank or of each tank that comprise at least one supply line extending from the or each tank to at least one filler opening located at the level of the third casing, passing within at least one of said arms connecting the second and third casings.

Abstract: A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.