Abstract: A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.

Abstract: A seal plate for directing an airflow includes a hub, main pumping vanes, and splitter vanes. The hub has a tubular section and an annular flange section flared outwardly relative to the tubular section to define a flow surface. The main pumping vanes are disposed circumferentially on the flow surface around the annular flange section and each has a canted section located radially inward relative to a straight section and aligned with a flow direction of the airflow. The straight section extends along a first plane including a centerline of the seal plate. The splitter vanes are disposed circumferentially on the flow surface around the annular flange section such that at least one splitter vane is disposed between the straight sections of two adjacent main pumping vanes. Each splitter vane has a length that is less than a length of each of the two adjacent main pumping vanes.

Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Abstract: A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

Abstract: An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

Abstract: An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

Abstract: An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, each wall including an interior surface that defines an interior with the edges, root and tip. The blade includes a plurality of independent cooling circuit flow paths within the blade interior and a roughened surface. The roughened surface is formed on an interior surface of at least one of the convex suction side wall and the concave pressure side wall, the roughened surface comprising a plurality of cylindrical depressions. Each depression includes a cylindrical wall coupled to a bottom wall by a chamfered edge formed therebetween, and the roughened surface defines at least a portion of one of the flow paths of the plurality of independent cooling circuit flow paths. Methods for forming the blade are also provided.