A baffle includes a disk, a rim, a peripheral portion, and an outlet. The rim is connected to and circumferentially surrounds a portion of the disk. The peripheral portion is connected to and circumferentially surrounds the rim. The peripheral portion forms a channel. The outlet is fluidly connected to the channel of the peripheral portion. The outlet includes a cover and a series of openings. The cover caps a distal end of the outlet. The series of openings is disposed on a portion of the outlet and is fluidly connected to the channel via the outlet.

A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

A geared turbofan engine includes a first spool including a first compressor and a first turbine. The first compressor is immediately before a combustor and the first turbine is immediately after the combustor. A second spool includes at least a second turbine disposed axially aft of the first turbine. A first tower shaft is engaged to drive the high speed spool. A second tower shaft engaged to be driven by the second spool. A starter is engaged to drive the first tower shaft. An accessory gear box is driven by the second tower shaft. A first clutch is disposed between the first tower shaft and the starter. The first clutch is configured to enable the starter to drive the high speed spool. A second clutch is disposed between the second tower shaft and the accessory gear box, the second clutch configured to enable the second spool to drive the accessory gear box. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

A turbomachine intermediate casing including an internal hub designed to accept a turbomachine compressor shaft, an outer shell ring, and a plurality of radial arms connecting the hub and the shell ring, one of the arms including an internal housing of radial shaft for driving auxiliary machines, the casing further includes a bevel gearbox for the radial shaft arranged in the outer shell ring, the gearbox being formed as one with the outer shell ring, and the bevel gearbox includes a housing for gears between a radial shaft and an accessories gearbox, the housing including an opening opening to the periphery of the outer shell ring.

A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.

A bowed rotor prevention system for a gas turbine engine includes a bowed rotor prevention motor operable to drive rotation of the gas turbine engine through an engine accessory gearbox. The bowed rotor prevention system also includes a controller operable to engage the bowed rotor prevention motor and drive rotation of the gas turbine engine below an engine starting speed until a bowed rotor prevention threshold condition is met.

A transmission system may include a first bevel gear, a second bevel gear and a baffle. The second bevel gear is meshed with the first bevel gear, and includes a plurality of gear teeth arranged in a circumferential array. The baffle includes a baffle wall and a baffle outlet. The baffle wall is arranged next to and covers a subset of the gear teeth. The baffle outlet forms a lubricant outlet passage that extends through the baffle wall.

A gearbox to be attached to a turbine engine to drive at least one apparatus annexed to the turbine engine, the gearbox including a housing; a power take-off member capable of engaging with a radial shaft of the turbine engine; at least one kinematic chain located inside the housing and capable of transmitting the rotational movement of the power take-off member to at least one rotatable shaft of an apparatus. The kinematic chain includes a first end and a second end. The power take-off member is linked to the kinematic chain by a gear having convergent axes and located between the first end and the second end of the kinematic chain.

An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.