Abstract: An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber directs cooling air inside the airfoil. The assembly comprises an impingement hole fluidly coupled with the cooling chamber. The impingement hole directs at least some of the cooling air out of the cooling chamber. A double impingement slot cap assembly forms a cover over the impingement hole. The double impingement slot cap assembly directs the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil.

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.

Abstract: A turbine component includes an internal surface, an external surface and a cooling hole. The cooling hole includes an inlet disposed on the internal surface, an outlet disposed on the external surface and a flow passage in fluid communication between the inlet and outlet. The flow passage includes a metering section extending from the inlet to a metering end, a diffusion zone extending from the metering end to the outlet, and a hooded region defined by a portion of the diffusion zone covered by a hood. The cooling hole also includes a vane extending across the flow passage, wherein a portion of the vane is disposed within the hooded region.

Abstract: A turbine component includes a rail coolant directing chamber radially outward from an airfoil chamber and radially inward from a tip plate. The chamber includes an inlet fluidly coupled to the airfoil chamber to receive a coolant flow therefrom. A plurality of outlets from the rail coolant directing chamber direct the coolant flow to the at least one rail cooling passage in the rail. At least one directing wall is within the rail coolant directing chamber to direct the coolant flow towards one or more of the plurality of outlets located along at least one of the pressure side wall and an aft region of the suction side wall prior to other outlets.

Abstract: Methods of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface, are disclosed. An opening is formed passing through the component wall and fluidly connecting the internal and external surfaces. The opening includes a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface. A preformed cap element is added to close a portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface. The preformed metal cap element includes a projection extending internally of the external surface and into the diffusion area to define an internally facing section of the diffusion section. The cooling passage extends through the component wall and fluidly connects the internal surface and the external surface.

Abstract: A turbine component includes a rail coolant directing chamber radially outward from an airfoil chamber and radially inward from a tip plate. The chamber includes an inlet fluidly coupled to the airfoil chamber to receive a coolant flow therefrom. A plurality of outlets from the rail coolant directing chamber direct the coolant flow to the at least one rail cooling passage in the rail. At least one directing wall is within the rail coolant directing chamber to direct the coolant flow towards one or more of the plurality of outlets located along at least one of the pressure side wall and an aft region of the suction side wall prior to other outlets.

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.

Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

Abstract: A cooling assembly comprises a cooling chamber disposed inside a turbine assembly. The cooling chamber is configured to direct cooling air inside one or more of a combustion chamber or an airfoil of the turbine assembly. An orthogonally converging diffusing (OCD) conduit is fluidly coupled with the cooling chamber. The OCD conduit is configured to direct at least some of the cooling air out of the cooling chamber outside of an exterior surface of the one or more of the combustion chamber or the airfoil. The OCD conduit is elongated along and encompasses an intersection between a constricting plane and a diffusing plane that are traverse to each other. The OCD conduit has an interior surface with a first distance between opposing first portions of the interior surface. The first distance increases in the diffusing plane at increasing distances along the intersection from the cooling chamber toward the exterior surface.

Abstract: An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber directs cooling air inside the airfoil. The assembly comprises an impingement hole fluidly coupled with the cooling chamber. The impingement hole directs at least some of the cooling air out of the cooling chamber. A double impingement slot cap assembly forms a cover over the impingement hole. The double impingement slot cap assembly directs the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil.

Abstract: The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate.

Abstract: A turbine component includes an internal surface, an external surface and a cooling hole. The cooling hole includes an inlet disposed on the internal surface, an outlet disposed on the external surface and a flow passage in fluid communication between the inlet and outlet. The flow passage includes a metering section extending from the inlet to a metering end, a diffusion zone extending from the metering end to the outlet, and a hooded region defined by a portion of the diffusion zone covered by a hood. The cooling hole also includes a vane extending across the flow passage, wherein a portion of the vane is disposed within the hooded region.

Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

Abstract: The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate.