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 engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The apparatus formed from a method including calculating a factor and adjusting a variable until the factor is between a given range.

A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

An apparatus and method for forming an engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The method including calculating a factor and adjusting a variable until the factor is between a given range.

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.

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 airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.

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.

A method for protecting a coating on a surface of a component is provided. The method includes a coating step for coating at least a portion of the component with a ceramic slurry. A projecting step is used for projecting a pattern of light onto the component with a lithographic process to expose and solidify a ceramic layer. A removing step is used for removing unexposed portions of the ceramic slurry from the component. A heating step heats the component to sinter the ceramic layer. The ceramic layer is formed with multiple fracture planes.

A lubrication system for an attritable engine includes a bearing chamber, a fluid filtering inlet configured to receive a fluid, and a fluid filtering outlet located downstream of the fluid filtering inlet and configured to deliver the fluid to the bearing chamber. The lubrication system also includes a lattice, integral and conformal with the attritable engine, configured to filter the fluid, and located between the fluid filtering inlet and the fluid filtering outlet. The lubrication system also includes a metering port, configured to meter the fluid and located downstream of the lattice and upstream of the fluid filtering outlet.