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A turbine blade is provided comprising an internal cavity into which cooling air is flowable, an external wall and a first, second and third cooling circuits embedded with the wall. The cooling circuits include inlets that connect each respective cooling circuit with a cavity to provide a cooling ai

A turbine blade is provided comprising an internal cavity into which cooling air is flowable, an external wall and a first, second and third cooling circuits embedded with the wall. The cooling circuits include inlets that connect each respective cooling circuit with a cavity to provide a cooling air flow path into the respective cooling circuit. The cooling circuits also include an exit aperture that provides a cooling air flow path out of the respective cooling circuits. The cooling circuits are configured to increase the temperature of the cooling air as it travels from the inlet to the exit aperture. In the exemplary embodiment, the inlets are aligned with the direction of counter-rotating flow circulations experienced by the inner surface of the wall caused by Coriolis flow effects on the cooling air flowing inside the cavity.

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1. A turbine rotor blade comprising:an external wall, said external wall includes an inner surface; an internal cavity into which cooling air is flowable; a first cooling circuit embedded within said wall, said first cooling circuit includes: a first inlet, said first inlet connects said first cooli

1. A turbine rotor blade comprising:an external wall, said external wall includes an inner surface; an internal cavity into which cooling air is flowable; a first cooling circuit embedded within said wall, said first cooling circuit includes: a first inlet, said first inlet connects said first cooling circuit with said cavity and provides a cooling air flow path into said first cooling circuit; and an exit aperture, said exit aperture provides a cooling air flow path out of said first cooling circuit, said first cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet to said exit aperture; a second cooling circuit embedded within said wall, said second cooling circuit includes: a first inlet, said first inlet of said second cooling circuit connects said second cooling circuit with said cavity and provides a cooling air flow path into said second cooling circuit; and an exit aperture, said exit aperture of said second cooling circuit provides a cooling air flow path out of said second cooling circuit, said second cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet of said second cooling circuit to said exit aperture of said second cooling circuit; and a third cooling circuit embedded within said wall, said third cooling circuit includes: a first inlet, said first inlet of said third cooling circuit connects said third cooling circuit with said cavity and provides a cooling air flow path into said third cooling circuit; and an exit aperture, said exit aperture of said third cooling circuit provides a cooling air flow path out of said third cooling circuit, said third cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet of said third cooling circuit to said exit aperture of said third cooling circuit; wherein said first inlets are aligned with the direction of counter-rotating flow circulations experienced by said inner surface of said wall of said cavity caused by Coriolis forces on the cooling air flowing inside said cavity. 2. The blade of claim 1, wherein said first, second and third cooling circuits include a plurality of pedestals spaced apart from one another and extending between first and second wall portions of said wall to define a pathway to turbulate the cooling air passing therebetween.3. A turbine blade comprising:first and second sidewalls extending longitudinally in span from root to tip, and extending in chord between leading and trailing edges, said sidewalls being spaced laterally apart between said leading and trailing edges, and joined together by chordally spaced apart partitions extending longitudinally between said root and tip to define an internal cavity into which cooling air is flowable; a first cooling circuit embedded within said first sidewall, said first cooling circuit includes: a first inlet, said first inlet connects said first cooling circuit with said cavity and provides a cooling air flow path into said first cooling circuit; and an exit aperture, said exit aperture provides a cooling air flow path out of said first cooling circuit, said first cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet to said exit aperture; a second cooling circuit embedded within said second sidewall, said second cooling circuit includes: a first inlet, said first inlet of said second cooling circuit connects said second cooling circuit with said cavity and provides a cooling air flow path into said second cooling circuit; and an exit aperture, said exit aperture of said second cooling circuit provides a cooling air flow path out of said second cooling circuit, said second cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet of said second cooling circuit to said exit aperture of said second cooling circuit; and a third cooling circuit embedded within said second sidewall, said third cooling circuit includes: a first inlet, said first inlet of said third cooling circuit connects said third cooling circuit with said cavity and provides a cooling air flow path into said third cooling circuit; and an exit aperture, said exit aperture of said third cooling circuit provides a cooling air flow path out of said third cooling circuit, said third cooling circuit configured to increase the temperature of the cooling air as it travels from said inlet of said third cooling circuit to said exit aperture of said third cooling circuit; wherein said first inlets are aligned with the direction of counter-rotating flow circulations experienced by inner surfaces of said sidewalls of said cavity caused by Coriolis forces on the cooling air flowing inside said cavity. 4. The blade of claim 3, wherein said first sidewall is a generally concave, pressure sidewall, and said second sidewall is a generally convex, suction sidewall and said first inlet of said first cooling circuit is positioned within a span along said pressure sidewall of about 20% on either side of a centerline that traverses said cavity, said centerline is perpendicular to the axis of rotation of the blade and extends through said sidewalls, andwherein said suction sidewall includes a first end and an opposing second end, said first inlet of said second cooling circuit is positioned within a span along said suction sidewall of about 40% from said first end of said suction sidewall and said first inlet of said third cooling circuit is positioned within a span along said suction sidewall of about 40% span from said second end of said suction sidewall; when the cooling air flow is radially outward in said cavity. 5. The blade of claim 3, wherein said first sidewall is a generally convex, suction sidewall, and said second sidewall is a generally concave, pressure sidewall and said first inlet of said first cooling circuit is positioned within a span along said suction sidewall of about 20% on either side of a centerline that traverses said cavity, said centerline is perpendicular to the axis of rotation of the blade and extends through said sidewalls, andwherein said pressure sidewall includes a first end and an opposing second end, said first inlet of said second cooling circuit is positioned within a span along said pressure sidewall of about 40% from said first end of said pressure sidewall and said first inlet of said third cooling circuit is positioned within a span along said pressure sidewall of about 40% span from said second end of said pressure sidewall; when the cooling air flow is radially inward in said cavity. 6. The blade of claim 3, wherein the blade is fabricated from a metal selected from the group consisting of nickel based alloys and cobalt based alloys.7. The blade of claim 4, wherein said exit aperture of said first cooling circuit is a film cooling slot, said film cooling slot radially extends through said pressure sidewall and discharges said cooling air from thereform, andwherein said exit apertures of said second and third cooling circuits are film cooling slots, said film cooling slots of said second and third cooling circuits radially extend through said suction sidewall, said film cooling slot of said second cooling circuit discharges the cooling air therefrom and said film cooling slot of said third cooling circuit discharges the cooling air thereform. 8. The blade of claim 7, wherein said film cooling slots of said second and third cooling circuits are radially staggered.9. The blade of claim 5, wherein said exit aperture of said first cooling circuit is a film cooling slot, said film cooling slot radially extends through said suction sidewall and discharges said cooling air from thereform, andwherein said exit apertures of said second and third cooling circuits are film cooling slots, said film cooling slots of said second and third cooling circuits radially extend through said pressure sidewall, said film cooling slot of said second cooling circuit discharges the cooling air therefrom and said film cooling slot of said third cooling circuit discharges the cooling air thereform. 10. The blade of claim 9, wherein said film cooling slots of said second and third cooling circuits are radially staggered.11. The blade of claim 5, further including a first turbulator positioned on said inner surface of said pressure sidewall adjacent and upstream of said first inlets of said second and third cooling circuits, and a second turbulator positioned on said inner surface of said suction sidewall adjacent and upstream of said first inlet of said first cooling circuit.12. The blade of claim 4, further including a first turbulator positioned on said inner surface of said suction sidewall adjacent and upstream of said first inlet of said first cooling circuit, and a second turbulator positioned on said inner surface of said pressure sidewall adjacent and upstream of said first inlets of said second and third cooling circuits.13. The blade of claim 3, wherein said first cooling circuit includes a second inlet, said first and second inlets of said first cooling circuit radially spaced apart.14. The blade of claim 3, wherein said first cooling circuit occupies a wall surface area no greater than about 0.06 square inches, said second cooling circuit occupies a wall surface area no greater than about 0.06 square inches, and said third cooling circuit occupies a wall surface area no greater than about 0.06 square inches.15. The blade of claim 13, wherein said first and second inlets are race track shaped whose length in the radial direction is greater than its width transverse to such direction.16. A method for placing inlets of cooling circuits in an exterior wall of a turbine blade to facilitate ingestion of cooling air into said cooling circuits, said wall having an inner surface and said blade having an internal cavity into which cooling air is flowable from an end of said cavity, the cavity in flow communication with the inlets, said method comprising:determining the flow direction of cooling air within said cavity; taking into account Coriolis flow effects in the cooling air caused by rotation of the blade; and placing said inlets aligned with the direction of counter-rotating flow circulations experienced by said inner surface of said wall caused by Coriolis forces on the cooling air flowing inside said cavity. 17. The method of claim 16, further including the steps of:placing a turbulator on said inner surface of said wall adjacent and upstream of one of said inlets. 18. The method of claim 16, wherein said wall includes first and second sidewalls extending longitudinally in span from root to tip, and extending in chord between leading and trailing edges, said sidewalls being spaced laterally apart between said leading and trailing edges, and joined together by chordally spaced apart partitions extending longitudinally between said root and tip to define said internal cavity, andwherein said first sidewall is a generally concave, pressure sidewall, and said second sidewall is a generally convex, suction sidewall and one of said inlets of a respective one of said cooling circuits is positioned within a span along said pressure sidewall of about 20% on either side of a centerline that traverses said cavity, said centerline is perpendicular to the axis of rotation of the blade and extends through said sidewalls, and wherein said suction sidewall includes a first end and an opposing second end, and one of said inlets of a respective one of said cooling circuits is positioned within a span along said suction sidewall of about 40% from said first end of said suction sidewall and one of said inlets of a respective one of said cooling circuits is positioned within a span along said suction sidewall of about 40% span from said second end of said suction sidewall; when the cooling air flow is radially outward in said cavity. 19. The method of claim 16, wherein said wall includes first and second sidewalls extending longitudinally in span from root to tip, and extending in chord between leading and trailing edges, said sidewalls being spaced laterally apart between said leading and trailing edges, and joined together by chordally spaced apart partitions extending longitudinally between said root and tip to define said internal cavity, andwherein said first sidewall is a generally convex, suction sidewall, and said second sidewall is a generally concave, pressure sidewall and one of said inlets of a respective one of said cooling circuits is positioned within a span along said suction sidewall of about 20% on either side of a centerline that traverses said cavity, said centerline is perpendicular to the axis of rotation of the blade and extends through said sidewalls, and wherein said pressure sidewall includes a first end and an opposing second end, and one of said inlets of a respective one of said cooling circuits is positioned within a span along said pressure sidewall of about 40% from said first end of said pressure sidewall and one of said inlets of a respective one of said cooling circuits is positioned within a span along said pressure sidewall of about 40% span from said second end of said pressure sidewall; when the cooling air flow is radially inward in said cavity. 20. The method of claim 16, wherein said blade is fabricated from a metal selected from the group consisting of nickel based alloys and cobalt based alloys.21. The method of claim 16, wherein one of said cooling circuits occupies a wall surface area no greater than about 0.06 square inches.22. The method of claim 16, wherein said inlets are race track shaped whose length in the radial direction is greater than its width transverse to such direction.