Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (?) with the heated surface.

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. One or more blades in the compressor or turbine sections has an internal cooling conduit with at least one of a bend or a terminal end. A plurality of cooling holes are provided in the blade, with each hole having an inlet fluidly coupled to the cooling conduit and an outlet opening onto an exterior of the blade.

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (?) with the heated surface.

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component 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.

Abstract: An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Abstract: An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component 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.