Abstract: A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

Abstract: A rotary component may comprising a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

Abstract: An assembly for use in an attritable engine includes a hub and a blade. The hub is configured to rotate about a centerline axis passing through a center of the hub and is formed with a first type of layer-by-layer additive manufacturing process. The blade is connected to and extends radially outward from the hub. The blade is formed with a second type of layer-by-layer additive manufacturing process that is different than the first layer-by-layer additive manufacturing process. The hub and the blade are integrally formed together as a single piece of material with a layer-by-layer additive manufacturing process. The blade includes a root of a first material, a platform connected to the root, an airfoil connected to and extending from the platform, and a tip connected on a distal end of the airfoil opposite from the root. The platform includes a material that is different from the first.

Abstract: A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.

Abstract: A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body.

Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.

Abstract: A tandem tip blade includes a main blade body, a front blade and a rear blade. The front blade extends from a main body end. Each of a front blade pressure and a front blade suction side extends between a front blade leading edge and a front blade trailing edge and a front blade tip extending from the front blade pressure side to the front blade suction side. The rear blade extends from the main body end. Each of a rear blade pressure side and a rear blade suction side extends between a rear blade leading edge and a rear blade trailing edge, and a rear blade tip extending from the rear blade pressure side to the rear blade suction side.

Abstract: A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body.

Abstract: A tandem tip blade includes a main blade body, a front blade and a rear blade. The front blade extends from a main body end. Each of a front blade pressure and a front blade suction side extends between a front blade leading edge and a front blade trailing edge and a front blade tip extending from the front blade pressure side to the front blade suction side. The rear blade extends from the main body end. Each of a rear blade pressure side and a rear blade suction side extends between a rear blade leading edge and a rear blade trailing edge, and a rear blade tip extending from the rear blade pressure side to the rear blade suction side.

Abstract: An exit nozzle section for an engine has an outer wall and an inner wall, and a plurality of exit guide vanes extending between the outer wall and the inner wall. Different ones of the exit guide vanes having different cambers in different regions of the exit nozzle section.

Abstract: A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.