A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

A component includes a component body. The component further includes a first passage disposed in the component body. The first passage includes a first end and a second end opposite the first end. The component further includes a second passage. The second passage extends from the second end of the first passage. The second passage includes a turn. The component further includes a third passage. The third passage extends from the second end of the first passage. The component further includes a first projection extending from a passage surface of the component body within the first passage. The first projection is disposed between the first and the second end of the first passage and is configured to direct debris transiting the first passage away from the second passage and into the third passage.

An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.

A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade, wherein at least one ventilation cavity is a ventilation cavity of a first type comprising at least one ascending portion which extends substantially longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and at least one discharge portion which extends substantially transversely and which opens at the trailing edge via at least one port of the trailing edge, and wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends substantially longitudinally from the apex, engaged with the upper surface wall and spaced from the lower.

A cooling structure for a trailing edge of a turbine blade is provided. The cooling structure for the trailing edge of the turbine blade comprising an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge, and a cavity channel formed in the blade part and through which a cooling fluid flows, the cooling structure including slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains, wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot, and wherein the cooling fluid is introduced through a micro-channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface.

A gas turbine engine article includes a substrate that has a pre-bond surface that includes a serpentine groove. A coating is disposed on the pre-bond surface and mechanically interlocks with the serpentine groove.

A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.