An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.

A nested segment assembly and a method of additively manufacturing the same are provided. In one example aspect, the nested segment assembly includes a first component segment and a segment component segment positioned adjacent the first component segment. The first component segment has an end face and a tongue projecting outwardly from the end face. The second component segment defines a groove. The groove is defined at an end face of the second component segment that is adjacent the end face of the first component segment. The first component segment and the second component segment are additively printed such that at least a portion of the tongue of the first component segment is nested within the groove defined by the second component segment. Segmented components having a tesla valve formed therebetween are also provided.

An engine component assembly for impingement cooling. The engine component assembly includes an engine first component having a cooled surface. The engine first component having a flow path on one side of the cooled surface. A second component is a disposed adjacent to the engine first component between the flow path and the engine first component, and has a plurality of openings forming an array through the second component. The cooling flow path passes through the plurality of openings to cool the cooled surface. The second component having a surface facing the cooled surface of the engine first component. A plurality of discrete cooling features that have at least one wall that has a curved cross-section extend from the second component surface into a gap between and toward the cooled surface of the engine first component and defining an array.

An air flow guide cap for inducing an air flow into a through hole of the floor includes: an upper surface upwardly inclined relative to a horizontal plane; and a wall surface downwardly extending along edges of the upper surface except the edge adjacent to an air inlet.

The disclosure relates to turbomachine components which include one or more coating-capturing features for thermal insulation. A turbomachine component may include: a body having an exterior surface positioned within a hot gas path (HGP) section of a turbomachine; and a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises: a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature, a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and an indentation positioned between the first and second members.

An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.

A wall of a hot gas part, having a first surface subjectable to a cooling fluid, a second surface located opposite of the first surface and subjectable to a hot gas and, at least one film cooling hole extending from an inlet area located within the first surface to an outlet area located within the second surface for leading the cooling fluid from the first surface to the second surface. The respective film cooling hole has a diffusor section located upstream of the outlet area, the diffusor section is bordered at least by a diffusor bottom and two opposing diffusor side walls, wherein the diffusor section has a delta wedge element for dividing the cooling fluid flow into two sub-flows and subsequent formation of a pair of delta vortices. The respective delta wedge element protrudes in a step-wise manner from the diffusor bottom and is, in a top view, triangular-shaped.

An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner surface facing away from the outer shell and an outer surface facing toward the outer shell, and the outer surface has one or more false flanges. At least one of the one or more false flanges includes a first surface protruding from the outer surface and facing the outer shell, and a flow diverting portion extending between the first surface and the outer surface of the inner shell. The flow diverting portion includes a first portion that diverges in a first circumferential direction between the first surface and the outer surface.