A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.

The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.

A vibrorotational fluid flow actuator includes: a first vibrorotational component comprising a first body including an axis, a plurality of first legs extending from a bottom surface of first body in a direction of and at an angle to the axis, and a plurality of first blades extending from a respective side of the first body in a direction perpendicular to the axis, wherein when the first vibrorotational component is placed on a chassis, vibration of the chassis induces rotation of the body such that the blades and body rotate about the axis of the body thereby inducing fluid flow in a fluid surrounding the actuator.

A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

A method of creating a component comprises forming a substrate and depositing a template material within the substrate, such that there are a plurality of template member. The component is heated to a temperature above a melting point of the template material, such that the template material wicks into a porosity of the substrate and forms a component with voids. An average hydraulic diameter of the voids is less than 1 millimeter.

A semi-passive cooling system for a component exposed to a fluid flow utilizes a hierarchical vasculature and a sacrificial transpirant to cool the component. The component includes a body that defines a transpirant reservoir and the hierarchical vasculature. The transpirant is configured to transition between a solid phase and a vapor phase over an operating temperature range of the component.

A manufacturing method includes forming one or more grooves in a component that comprises a substrate with an outer surface. The substrate has at least one interior space. Each groove extends at least partially along the substrate and has a base and a top. The manufacturing method further includes applying a structural coating on at least a portion of the substrate and processing at least a portion of the surface of the structural coating so as to plastically deform the structural coating at least in the vicinity of the top of a respective groove, such that a gap across the top of the groove is reduced. A component is also disclosed and includes a structural coating disposed on at least a portion of a substrate, where the surface of the structural coating is faceted in the vicinity of the respective groove.

A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further having a composite assembly provided within at least one of the fan section, the compressor section, the combustion section or the turbine section. The composite assembly including a set of stacked composite plies, with each ply of the set of stacked composite plies being made from a plurality of fibers.

An example gas turbine engine component includes a component configured to separate a cooling air plenum from a heated gas environment. The component includes a substrate defining a surface, and a unitary structure. The unitary structure includes a cooling region and a cover layer. The cover layer defines a hot wall surface configured to face the heated gas environment. The cooling region is disposed between the cover surface and the substrate and includes a plurality of support structures extending between the cover layer and the surface of the substrate. At least some of the support structures define a respective bond surface bonded to the substrate at the surface of the substrate. An example technique for fabricating the gas turbine engine component includes additively depositing the unitary structure on the surface of the substrate.