Abstract: A turbine engine component, such as a blade or a vane, is provided by the present invention. The turbine engine component has a pressure side and a suction side. Each of the pressure and suction sides has an external wall and an internal wall. A first set of fluid passageways is located on the pressure side between the external wall and the internal wall. A second set of fluid passageways is located on the suction side between the external wall and the internal wall. Each of the fluid passageways in the first set and in the second set has a wavy configuration. The turbine engine component may also have one or more wavy trailing edge cooling passageways for cooling a trailing edge portion of the component.

Abstract: An internally-cooled turbomachine element has an airfoil extending between inboard and outboard ends. A cooling passageway is at least partially within the airfoil and has at least a first turn. Means are in the passageway for limiting a turning a loss of the first turn. The turbomachine element may result from a reengineering of an existing element configuration lacking such means.

Abstract: A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: According to the present invention, a cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

Abstract: A coolable airfoil is disclosed which includes an internal cavity, an external wall, a plurality of first apertures, and a plurality of second apertures. The external wall includes a suction-side portion and a pressure-side portion. The external wall portions extend chordwise between a leading edge and a trailing edge, and spanwise between an inner radial surface and an outer radial surface. The mean camber line of the airfoil passes through the leading edge and the trailing edge along a path equidistant between the outer surfaces of the pressure-side and suction-side walls. The first apertures, which are disposed in the external wall adjacent the trailing edge, extend a distance within the suction-side wall portion and exit the external wall through the pressure-side wall portion. The second apertures extend through the pressure-side wall portion and exit the pressure-side wall portion upstream of and in close proximity to the first apertures.

Abstract: A coolable airfoil is provided which includes an internal cavity, an external wall, a plurality of first cooling apertures, and a plurality of second cooling apertures. The external wall includes a suction side portion and a pressure side portion. The wall portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. The first cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the pressure side portion. The second cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the suction side portion.