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 component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

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 apparatus and method relating an airfoil for a turbine engine with an outer wall 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 includes a first cooling passage extending in the span-wise direction within the interior and a second cooling passage defining an impingement surface and located proximate the first cooling passage, an interior wall separating the first cooling passage from the second cooling passage, and at least one cooling hole passing through the interior wall.

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 component for a turbine engine includes a body having a wall at least partially defining an interior and separating a combustion air flow path from a cooling air flow path. The component also includes at least one fluid inlet supplying cooling air to the interior of the body, as well as a cyclone separator.

Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.

Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Abstract: Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.

Abstract: An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.

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: 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: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Abstract: An apparatus and method of forming an engine component having an outer wall forming an interior. The interior can be separated into two or more flow paths or flow channels. The two flow paths can be formed by casting having one or more core ties connecting the flow paths during casting. One or more core tie holes can be formed remnant of the core ties during casting in order to fluidly couple the two or more flow paths or flow channels.

Abstract: A component for a turbine engine includes a body having a wall separating a combustion air flow path from a cooling air flow path. The component can include an isolation chamber formed in the cooling air flow path. The component can also include at least one cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path.

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 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, 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 in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.

Abstract: An apparatus and method for minimizing a cross-flow across an engine cooling hole can include a component, such as an airfoil, having an outer wall bounding an interior from an exterior. A cooling passage is formed in the interior of the component for cooling the engine component. A cooling hole or film hole can be provided in the outer wall fluidly coupling the interior to the exterior. The cooling passage can be shaped to minimize cross-flow over the cooling hole at the interior of the component.

Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.