Abstract: Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.

Abstract: An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.

Abstract: The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with a relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased.

Abstract: The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased.

Abstract: A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.

Abstract: Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.

Abstract: A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.

Abstract: An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.

Abstract: A cooling hole for a gas turbine engine component has a bi-lobed shape to improve cooling effectiveness. The gas turbine engine component has a first outer surface and a second outer surface separated from each other by a thickness. The cooling hole extends through the thickness from a first opening at the first outer surface to a second opening at the second outer surface. The first and second openings are defined by shapes that are different from each other. One of the first and second openings has the bi-lobed shape.

Abstract: A cooled airfoil 10 has an internal fluid passage 34 that includes upstream and downstream legs, such as a co-centrifugal leg 40 and a counter-centrifugal leg 42. The legs are separated from each other by a rib 44 but are connected in series with each other. The airfoil also includes a vent passage 56 for venting fluid from the internal passage. The intake 60 to the vent passage resides in the counter-centrifugal leg. The vent at least partially counteracts the separation potential of a separation susceptible region 54 by allowing some of the coolant to vent from the passage leg 42.

Abstract: The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with a relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased.

Abstract: The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a descending flank 52 and an ascending flank 54. Coolant holes 60, which penetrate through the wall, have discharge openings residing on the ascending flank 54. During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets 70 concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression 48 is a trough 50. In another embodiment, the depression is a dimple 72.

Abstract: The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a descending flank 52 and an ascending flank 54. Coolant holes 60, which penetrate through the wall, have discharge openings residing on the ascending flank 54. During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets 70 concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression 48 is a trough 50. In another embodiment, the depression is a dimple 72.

Abstract: The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a descending flank 52 and an ascending flank 54. Coolant holes 60, which penetrate through the wall, have discharge openings residing on the ascending flank 54. During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets 70 concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression 48 is a trough 50. In another embodiment, the depression is a dimple 72.

Abstract: The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a descending flank 52 and an ascending flank 54. Coolant holes 60, which penetrate through the wall, have discharge openings residing on the ascending flank 54. During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets 70 concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression 48 is a trough 50. In another embodiment, the depression is a dimple 72.