A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.

An engine case is provided having a first solid wall region and a second solid wall region with an internal region between the first and second sold wall regions. The internal region defines at least one cavity. One or more lattice structures are provided within the cavity that controls the flow of coolant air through the cavity. The cavity may be divided into two or more distinct cooling regions for allowing particular coolant flow paths to be provided to different parts of the engine case.

A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components.

A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.

An article, a component, and a method of making a component are provided. The article includes a pre-sintered preform having a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component and the contoured distal face is arranged and disposed to form an exterior surface including a modified surface characteristic. The component includes a first end wall, a second end wall, and an article secured to at least one of the first end wall and the second end wall, the article including a pre-sintered preform having a contoured proximal face and a contoured distal face. The contoured proximal face substantially mirrors a contour of at least one of the first end wall and the second end wall, and the contoured distal face is arranged and disposed to form an exterior surface thereover.

A cooled gas turbine engine component includes a wall having a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture includes an inlet portion, a collection chamber, a metering portion, a U-shaped bend portion and a diffusing portion arranged in flow series from the inlet to the outlet. The inlet portion of each aperture is arranged substantially perpendicularly to a surface of the collection chamber. The metering portion of each aperture is arranged to extend longitudinally from a first lateral side of the collection chamber and the diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a quadrilateral shape in the second surface of the wall and each outlet is displaced laterally from the metering portion.

An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

A gas turbine engine includes an electrical device and a microchannel cooling system in communication with the electrical device to remove heat.

A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

A coolable component for a streaming engine providing an improved cooling, wherein the coolable component includes an outer wall providing an outer surface adapted to be in contact with a hot fluid like a hot gas stream used in the streaming engine or to be coated with a coating that is adapted to be in contact with the hot fluid, wherein the outer surface is at least partially curved. The coolable component includes at least one cooling channel inside the outer wall adapted to guide a cooling fluid through the cooling channel to cool the outer wall during operation of the streaming engine, wherein the cooling channel is adapted to provide a convection cooling of the outer surface.