Abstract: A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

Abstract: A turbine blade includes an airfoil section, wherein at least one cooling hole is formed a tip floor of the airfoil section, which is fluidically connected to an internal coolant cavity of the airfoil section. The turbine blade further includes an additively manufactured tip cap formed via layer-by-layer deposition of material directly over the tip floor of the airfoil section. The tip cap includes at least one squealer tip rail extending outward from the tip floor. The at least one squealer tip rail comprises an embedded cooling channel formed therein. The embedded cooling channel is aligned with and fluidically connected to the at least one cooling hole formed through the tip floor of the airfoil section. The embedded cooling channel comprises one or more outlets located on at least one of a side face and a top face of the at least one squealer tip rail.

Abstract: A turbine blade includes an airfoil section, wherein at least one cooling hole is formed a tip floor of the airfoil section, which is fluidically connected to an internal coolant cavity of the airfoil section. The turbine blade further includes an additively manufactured tip cap formed via layer-by-layer deposition of material directly over the tip floor of the airfoil section. The tip cap includes at least one squealer tip rail extending outward from the tip floor. The at least one squealer tip rail comprises an embedded cooling channel formed therein. The embedded cooling channel is aligned with and fluidically connected to the at least one cooling hole formed through the tip floor of the airfoil section. The embedded cooling channel comprises one or more outlets located on at least one of a side face and a top face of the at least one squealer tip rail.

Abstract: A composite layer system is presented. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features.

Abstract: A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

Abstract: A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device.

Abstract: A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device.

Abstract: A blade or a vane component of a turbomachine includes an inner space between two opposite inner walls of the component, and a plurality of ribs projecting from the two opposite inner wall forming a plurality of channels on each of the two opposite inner walls to guide the cooling fluid towards the trailing edge. The inner space is divided into a leading section towards the leading edge of the component and a trailing section towards the trailing edge of the component. The ribs are arranged in the leading section. A plurality of pin-fins projecting from the two opposite inner walls is arranged in the trailing section in a discrete manner.

Abstract: A blade or a vane component of a turbomachine includes an inner space between two opposite inner walls of the component, and a plurality of ribs projecting from the two opposite inner wall forming a plurality of channels on each of the two opposite inner walls to guide the cooling fluid towards the trailing edge. The inner space is divided into a leading section towards the leading edge of the component and a trailing section towards the trailing edge of the component. The ribs are arranged in the leading section. A plurality of pin-fins projecting from the two opposite inner walls is arranged in the trailing section in a discrete manner.