A method of assembling an epicyclic gear train includes positioning a carrier, the carrier being a unitary structure with side walls and mounts unitary with one another, inserting intermediate gears through a central opening of the carrier, moving each of the intermediate gears into intermediate gear pockets, inserting baffles into the carrier, inserting a sun gear through the central opening, and moving the intermediate gears to intermesh with the sun gear, and moving a ring gear into engagement with the intermediate gears.

An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

A method of assembling an epicyclic gear train includes positioning a carrier, the carrier being a unitary structure with side walls and mounts unitary with one another, inserting intermediate gears through a central opening of the carrier, moving each of the intermediate gears into intermediate gear pockets, inserting baffles into the carrier, inserting a sun gear through the central opening, and moving the intermediate gears to intermesh with the sun gear, and moving a ring gear into engagement with the intermediate gears.

A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.

An acoustic core has a plurality of cell walls formed of an additive-manufacturing material and a resonant space defined by the plurality of cell walls. At least some of the resonant cells have a multitude of sound-attenuating protuberances formed of the additive-manufacturing material of the cell walls protruding into the resonant space with a random or semi-random orientation and/or size. The sound-attenuating protuberances may be formed by orienting an additive-manufacturing tool with respect to a toolpath to form a contour of a workpart, in which the toolpath includes a plurality of overlapping toolpath passes configured so as to intentionally introduce an amount of additive-manufacturing material to the workpart that exceeds a domain occupied by the contour. As the amount of additive-manufacturing material intentionally introduced exceeds the domain occupied by the contour, a portion of the additive-manufacturing material may incidentally form the plurality of sound-attenuating protuberances.

A spray tip for a fluid applicator includes a stem configured to be inserted into the fluid applicator. The stem includes a stem pre-orifice portion and an insert receiving portion. The spray tip includes a pre-orifice insert having an inlet and an outlet. The pre-orifice insert is disposed within the insert receiving portion and disposed against a rearward shoulder of the stem.

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

A method of assembling an epicyclic gear train includes providing a unitary carrier that includes spaced apart walls and circumferentially spaced mounts interconnecting the walls, spaced apart apertures provided between the mounts at an outer circumference of the carrier, gear pockets provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls, inserting an intermediate gear through the central opening and moving the intermediate gear radially into the gear pocket to extend through the aperture, inserting a baffle into the carrier, and inserting a sun gear through the central opening to intermesh with the intermediate gear.

A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.