A gas turbine engine includes a planetary gear system including a sun gear, intermediate gears, and a ring gear. A lubricant recovery system for the planetary gear system includes fluid passages that extend through the planetary gear system. A gutter is located radially outward from the planetary gear system for collecting lubricant. At least a portion of the gutter is rigidly attached to the ring gear.

A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.

A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.

A planetary gear system for a gas turbine engine with a plurality of planetary gears coupled to a carrier device, with front planetary gears mounted on pins in a front row and aft planetary gears mounted on pins in an aft row, the two rows being parallel to each other in the axial direction of the planetary gear system. The carrier device includes a base structure being in one piece with the carrier device, the base structure positioned around a rotational axis of the gas turbine engine. The pins are coupled to the carrier device through first and second extension elements for the positioning of the pins relative to the base structure. The second extension elements axially extending the respective pins further away from the base structure than the pins positioned by the first extension elements.

A turbine engine duct assembly including a joint assembly having an outer shroud, a bellows, a flared tube, a backing ring, and a kinematic ring. The joint assembly provides for dynamic movement of the duct assembly during operation of the engine. Such dynamic movement can be resultant of vibrational forces or thermal expansion of the engine. The joint assembly permits such dynamic movement without excessive system stiffness.

A planet carrier for a mechanical gearbox of a turbomachine, in particular for an aircraft, the planet carrier being formed in a single piece and comprising two annular flasks connected by material bridges and together defining housings configured to receive planet gears, the flasks comprising orifices for mounting the planet gears which are oriented axially and which open into the housings. One of the flasks can include at least one thinning around its orifices, the at least one thinning defining a minimum thickness of material in the axial direction which is less than a minimum thickness of the other flask around each of its orifices.

A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned along the radial direction such that the area available to capture foreign object debris is minimized.

A seal assembly is disclosed. A seal assembly may comprise a seal carrier, a compliant structure comprising a first end and a second end, wherein the first end is coupled to the seal carrier, and/or a support structure coupled to the second end. The seal carrier may be integral with the compliant structure.

A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.

A turbocharger unit (10) incorporating variable turbine geometry. The unit (10) has a turbine housing (12) for receiving exhaust gases from an engine, a turbine wheel (14) located inside a turbine housing (12), and a bearing housing (24) connected to the turbine housing (12), having a recessed portion (28). A spring member is located in the recessed portion (28), and a heat shield (32) receives apply force from the spring member. There is also a cartridge for providing variable turbine geometry located in the turbine housing (12); the cartridge is held in contact with the turbine housing (12) by the spring member in the form of a contoured sleeve (26). The apply force received by the heat shield (32) from the spring member transfers through the cartridge, and holds the cartridge in place in the turbine housing.