An airfoil (10) for a turbine engine includes an array of features (22) positioned in an interior portion (11) of the airfoil (10). Each feature (22) extends from a pressure (14) side to a suction side (16). The array includes multiple radial rows (A-N) of features (22) with the features (22) in each row (A-N) being interspaced radially to define coolant passages (24) therebetween. The radial rows (A-N) are spaced along a forward-to-aft direction toward an airfoil trailing edge (20). The coolant passages (24) of the array are fluidically interconnected to lead a pressurized coolant toward the trailing edge (20) via a serial impingement on to the rows of features (22). The coolant passages (24) are geometrically configured to bias a coolant flow therethrough toward a first side (14) in relation to a second side (16) of the outer wall (12) to effect a greater cooling of the first side (14) than the second side (16).

A turbine engine, such as a gas turbine engine for an aircraft, can include a compressor section, a combustion section, and a turbine section in axial arrangement. The compressor and turbine sections can include a rotating disk having a plurality of blades and a stationary band having a plurality of stationary vanes. The disk and band are spaced axially defining a buffer cavity. One or more extensions extend into the buffer cavity to prevent ingestion of heated gas into the buffer cavity. Recesses on the underside of the extensions can improve the heat transfer coefficient for the extensions.

Various embodiments include a rotor key member having: a body with a primary axis extending in a direction substantially perpendicular to an axial direction in a steam turbine, the body including: a first pair of opposing sides; a second pair of opposing sides extending between the first pair of opposing sides; a top surface and a bottom surface extending between the second pair of opposing sides; and a fillet, bevel or chamfer edge extending between a first one of the first pair of opposing sides and the bottom surface and extending an entire length of the body along the primary axis; and a slot within the body, the slot extending a portion of a length of the body along the primary axis between the second pair of opposing sides and forming an opening in a second one of the first pair of opposing sides.

A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades.

A cut-back of a blade or vane in a gas turbine may comprise a first sidewall; a plurality of trailing ribs extended from the first sidewall and arranged along an end of the first sidewall; a second sidewall separated from the first sidewall, having a longer tail than the first sidewall and in contact with the plurality of trailing ribs; and one or more cut-back blocks extended between two trailing ribs along the inner surface of the second sidewall. The cut-back of the blade or vane may reduce the weight through the trailing ribs and the cut-back blocks formed at the trailing edge, and improve a heat transfer effect while retarding crack growth.

The present disclosure is directed to a nozzle for a turbomachine. The nozzle includes an inner side wall, an outer side wall radially spaced apart from the inner side wall, and an airfoil extending radially from the inner side wall to the outer side wall. The airfoil defines a cavity that extends radially through the nozzle. The cavity is at least partially defined by a cavity wall. The cavity wall at least partially defines a pocket in fluid communication with the cavity. A cooling passage is defined by one of the inner side wall or the outer side wall. The cooling passage is in fluid communication with the cavity via the pocket.

A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.

The present disclosure is directed to a composite component for a gas turbine engine. The composite component includes a composite wall having a flow side surface and non-flow side surface. The non-flow side surface includes at least one composite cooling projection positioned on and extending outwardly from the non-flow side surface.

Various embodiments include a rotor key member having: a body with a primary axis extending in a direction substantially perpendicular to an axial direction in a steam turbine, the body including: a first pair of opposing sides; a second pair of opposing sides extending between the first pair of opposing sides; a top surface and a bottom surface extending between the second pair of opposing sides; and a fillet, bevel or chamfer edge extending between a first one of the first pair of opposing sides and the bottom surface and extending an entire length of the body along the primary axis; and a slot within the body, the slot extending a portion of a length of the body along the primary axis between the second pair of opposing sides and forming an opening in a second one of the first pair of opposing sides.