A gas turbine engine configured with an engine core. A fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox arranged to receive an input from the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox comprising a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted, the planet carrier having an effective linear torsional stiffness and the gearbox having a gear mesh stiffness between the planet gears and the ring gear. Additionally, the product of the effective linear torsional stiffness of the planet carrier and the gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 5.0×10.sup.18 N.sup.2m.sup.−2.

An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.

A turbo machine including a plenum is formed within a double wall structure including an opening configured to provide fluid communication of a first flow of fluid between the plenum through the double wall structure, and an outer wall forming a passage configured to receive a second flow of fluid separate from the first flow of fluid, wherein a flowpath structure is formed at least in part within an inner wall, the flowpath structure configured to receive a third flow of fluid therethrough, the third flow of fluid separate from the first flow of fluid, the flowpath structure comprising an exit opening configured to provide fluid communication from the flowpath structure to the flowpath.

An airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

A turbine system includes a foam generating assembly having an in situ foam generating device at least partially positioned within the fluid passageway of the turbine engine, such that the in situ foam generating device is configured to generate foam within the fluid passageway of the turbine engine.

A gear reduction includes a sun gear that engages a plurality of planet gears mounted on a carrier. The planet gears are engaged with a ring gear. The ring gear is fixed against rotation such that rotation of the sun gear causes rotation of the planet gears to cause rotation of the carrier. There are spray bars positioned circumferentially between adjacent ones of the planet gears. The spray bars have jet openings, such that lubricant can be passed directly onto teeth on the sun gear. One of the side faces has a plurality of windows such that oil can be scavenged. There are side surfaces between plurality of windows that do not have an opening. A gas turbine engine and a spray bar are also disclosed.

A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.

A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.

Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises:- an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm.sup.2, and - an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

A tool for performing inspection and/or maintenance operations on an engine defines a longitudinal direction and a tangential direction. The tool includes a base extending along the longitudinal direction and including a body, a first extension member extending from the body in the tangential direction at a first location, and a second extension member extending from the body in the tangential direction at a second location. The second location is spaced from the first location along the longitudinal direction. The tool also includes a pivot member rotatably coupled to the base and moveable between an insertion position in which the pivot member is oriented generally along the longitudinal direction and a deployed position in which the pivot member is oriented away from the longitudinal direction.