Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. A casing apparatus for an aircraft engine includes a containment casing including a ridge on an exterior surface of the containment casing, and a deflector plate including a first end and a second end, the first end coupled to the ridge, the second end uncoupled to the containment casing.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.

Abstract: A fluid duct includes a body and an elongate rib. The body extends along a central axis and defines a lumen configured to receive a first fluid extending therethrough. The body has an inner surface and an outer surface. The central axis defines an axial direction along the central axis, a radial direction perpendicular to the central axis, and a circumferential direction oriented rotationally about the central axis. The elongate rib is positioned on the inner surface of the body and extends radially inward from the inner surface of the body. The elongate rib defines a channel extending through the elongate rib in a primary direction. The channel is configured to receive a second fluid and isolate the second fluid from the first fluid.

Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: Layered barrier cans and methods of producing the same are disclosed herein. An example shroud disclosed herein includes an inner shell including a first non-metallic material, an outer shell including the first non-metallic material or a second non-metallic material, and a metal core shell positioned between the inner shell and the outer shell.

Abstract: A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.

Abstract: A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.