Abstract: An intermediate investment casting mold includes at least a shell and a core. The shell has an outer surface and an inner surface, with the inner surface defining an interior for the shell. The core is located in the interior of the shell and is at least partially spaced from the inner surface of the shell. A void can be defined as the space between the core and the inner surface. The intermediate investment casting mold can include a plurality of anchors.

Abstract: A sealing apparatus for an axial flow turbomachine is disclosed. An example axial flow turbomachine includes band segments bordering a flow path, a first spline seal disposed at a first angle within a first slot of the band segments, a second spline seal disposed at second angle within a second slot of the band segments, a Z-seal disposed across a gap between the first slot and the second, the Z-seal positioned at least partially within the first slot and the second slot. The Z-seal includes a first segment disposed at the first angle at least partially within the first slot, the first segment to contact the first spline seal, a second segment disposed at the second angle at least partially within the second slot, a portion of the second segment in connection with a portion of the first segment, the second segment to contact the second spline seal.

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 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 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: A sealing apparatus for an axial flow turbomachine is disclosed. An example axial flow turbomachine includes band segments bordering a flow path, a first spline seal disposed at a first angle within a first slot of the band segments, a second spline seal disposed at second angle within a second slot of the band segments, a Z-seal disposed across a gap between the first slot and the second, the Z-seal positioned at least partially within the first slot and the second slot. The Z-seal includes a first segment disposed at the first angle at least partially within the first slot, the first segment to contact the first spline seal, a second segment disposed at the second angle at least partially within the second slot, a portion of the second segment in connection with a portion of the first segment, the second segment to contact the second spline seal.

Abstract: According to various embodiments, an airfoil includes an outer wall defining an airfoil body surrounding at least one cavity and a removable insert including at least one mating feature for coupling the removable insert with the airfoil body between a first location within the at least one cavity and a second location within the at least one cavity. The removable insert is free of openings and separates a first air flow path from a second air flow path through the at least one cavity. Vanes and gas turbine engines including the airfoil are also disclosed.

Abstract: A method and sling for supporting a tissue or other lumen in a body. When the sling is used to support the urethra of a female, it is effective in treating urinary incontinence. In one embodiment, the invention is a sling comprising a first end portion and a second end portion; and a support section intermediate the first and second end portions for supporting a tissue (preferably a urethra), the support section having first and second occluding portions and a relief portion intermediate the first and second occluding portions. In another aspect, the invention is a method of using the sling to support and occlude a urethra.