Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

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: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

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 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 valve orifice insert has a stepped-shaped wall including a first tubular section and a second tubular section having a smaller outer dimension than the first tubular section, and a lip structure protruding axially and including a planar valve seat surface. The first tubular section and the second tubular section being are joined by a step structure. At least one circumferential protrusion extends radially outward a predetermined distance from an outer surface of the first tubular section or an outer surface of the second tubular section to form an interference fit with the step-shaped opening when the valve orifice insert is fitted into the step-shaped opening.

Abstract: A valve orifice insert has a stepped-shaped wall including a first tubular section and a second tubular section having a smaller outer dimension than the first tubular section, and a lip structure protruding axially and including a planar valve seat surface. The first tubular section and the second tubular section being are joined by a step structure. At least one circumferential protrusion extends radially outward a predetermined distance from an outer surface of the first tubular section or an outer surface of the second tubular section to form an interference fit with the step-shaped opening when the valve orifice insert is fitted into the step-shaped opening.

Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.

Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.

Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further comprising at least one cooling passage extending radially within the interior and defining a primary cooling airflow; and at least one cooling hole having an inlet defining a first cross-sectional area, the inlet in communication with the cooling passage, an outlet defining a second cross-sectional area greater than the first cross-sectional area; wherein the primary cooling airflow enters the inlet in a first direction and exits the outlet in a second direction different than the first direction.

Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

Abstract: An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side extending between a leading edge and a trailing edge to define a chord-wise direction; at least one cooling conduit located within the interior and fluidly coupled to the cooling airflow. A primary cooling passage having at least one inlet fluidly coupled to the at least one cooling conduit, a primary outlet on the outer surface. A passage connecting the at least one inlet to the primary outlet, the passage separated into a first portion and a second portion. The primary outlet spaced from the trailing edge a predetermined distance.

Abstract: An apparatus and method for an engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow. The engine component including a wall defining an interior and having an outer surface. A tip wall spanning first and second sides of the wall to close the interior. A tip rail extending from the tip wall and having an inner tip rail surface, which in combination with the tip wall, at least partially bounds a region defining a plenum. A rim formed in at least one of the outer surface and inner tip rail surface.

Abstract: A turbine engine airfoil and method of cooling includes an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The airfoil can also include at least one cooling conduit and an impingement zone located within the at least one cooling conduit.

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.