초록 ▼

A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between

A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.

대표청구항 ▼

What is claimed is: 1. A method for fabricating a turbine rotor blade, said method comprising: casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, an airfoil, and at l

What is claimed is: 1. A method for fabricating a turbine rotor blade, said method comprising: casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, an airfoil, and at least one channel having an exit positioned in flow communication with the cast-in plenum and an entrance positioned in a dovetail lower surface, wherein the at least one channel extends from the entrance to the cast-in plenum to enable cooling air to flow directly from the entrance into the cast-in plenum; and forming a plurality of openings extending between the cast-in plenum and at least one of the platform inner surface and the platform outer surface, such that the at least one channel facilitates channeling cooling air through the plurality of openings to an exterior surface of the platform. 2. A method in accordance with claim 1 wherein casting a turbine rotor blade further comprises casting the turbine rotor blade to include a first plenum portion, a second plenum portion, and a third plenum portion that is coupled in flow communication with the first and the second plenum portions. 3. A method in accordance with claim 1 wherein casting a turbine rotor blade further comprises casting turbine rotor blade to include a first plenum portion, a second plenum portion, a first channel extending between the dovetail lower surface and the cast-in plenum first portion, and a second channel extending between the dovetail lower surface and the cast-in plenum second portion. 4. A method in accordance with claim 3 wherein casting a turbine rotor blade further comprises casting the turbine rotor blade to include a first channel extending between the dovetail lower surface and the cast-in plenum first portion, and a second channel extending between the dovetail lower surface and the cast-in plenum second portion, the first and second channels extending along at least one of a platform upstream side and a platform downstream side. 5. A method in accordance with claim 3 wherein casting a turbine rotor blade further comprises casting the turbine rotor blade to include a first channel extending between the dovetail lower surface and the cast-in plenum first portion, and a second channel extending between the dovetail lower surface and the cast-in plenum second portion, the first channel extending along at least one of a platform upstream side and a platform downstream side, the second channel extending along at least one of a platform upstream side and a platform downstream side opposite the first channel. 6. A method in accordance with claim 1 wherein casting a turbine rotor blade further comprises casting the turbine rotor blade to include a first plenum portion including a first side that is substantially concave, and a second plenum portion having a first side that substantially convex, the first and second plenum portions each including a plurality of openings selectively sized to facilitate channeling a predetermined quantity of cooling air to an exterior surface of the platform. 7. A method in accordance with claim 1 wherein casting a turbine rotor blade further comprises casting the turbine rotor blade to include a platform including a substantially solid portion and a substantially U-shaped cast-in plenum extending around the solid portion and between the platform outer surface and the platform inner surface, wherein the solid portion facilitates increasing a structural integrity of the turbine rotor blade. 8. A turbine rotor blade comprising: a dovetail; a platform coupled to said dovetail, said platform comprising a cast-in plenum formed within said platform; an airfoil coupled to said platform; at least one channel comprising an exit positioned in flow communication with said cast-in plenum and an entrance positioned in with a dovetail lower surface, said at least one channel extending from said entrance to the cast-in plenum to enable cooling air to flow directly from said entrance into said cast-in plenum; and a cooling source coupled in flow communication to said cast-in plenum. 9. A turbine rotor blade in accordance with claim 8 wherein said cast-in plenum comprises a first plenum portion, a second plenum portion, and a third plenum portion coupled in flow communication with said first and said second plenum portions. 10. A turbine rotor blade in accordance with claim 8 further comprising a first plenum portion, a second plenum portion, a first channel that extends between said dovetail lower surface and said cast-in plenum first portion, and a second channel that extends between said dovetail lower surface and said cast-in plenum second portion. 11. A turbine rotor blade in accordance with claim S wherein said turbine rotor blade further comprises a first channel extending between said dovetail lower surface and a cast-in plenum first portion, and a second channel extending between said dovetail lower surface and a cast-in plenum second portion, said first and second channels extending along at least one of a platform upstream side and a platform downstream side. 12. A turbine rotor blade in accordance with claim 8 wherein said turbine rotor blade further comprises a first channel extending between said dovetail lower surface and a cast-in plenum first portion, and a second channel extending between said dovetail lower surface and a cast-in plenum second portion, said first channel extends along at least one of a platform upstream side and a platform downstream side, said second channel extends along at least one of said platform upstream side and said platform downstream side opposite said first channel. 13. A turbine rotor blade in accordance with claim 8 wherein said cast-in plenum further comprises a first plenum portion comprising a first side that includes a generally concave profile, a second plenum portion comprising a first side that includes a generally convex profile, and a plurality of openings extending between said cast-in plenum and a platform outer surface, said plurality of openings sized to facilitate channeling a predetermined quantity of cooling air to said platform outer surface. 14. A turbine rotor blade in accordance with claim 8 wherein said platform comprises a substantially solid portion and a substantially U-shaped cast-in plenum extending around said solid portion, wherein said solid portion facilitates increasing a structural integrity of said turbine rotor blade. 15. A gas turbine engine rotor assembly comprising: a rotor; and a plurality of circumferentially-spaced rotor blades coupled to said rotor, each said rotor blade comprising a dovetail, a platform coupled to said dovetail, said platform comprising a cast-in plenum formed within said platform, an airfoil coupled to said platform, at least one channel comprising an exit positioned in flow communication with said cast-in plenum and an entrance positioned in a dovetail lower surface, said at least one channel extending from said entrance to said cast-in plenum, and a cooling source coupled in flow communication to said cast-in plenum such that cooling air flows directly from said entrance into said cast-in plenum. 16. A gas turbine engine rotor assembly in accordance with claim 15 wherein said cast-in plenum comprises a first plenum portion, a second plenum portion, and a third plenum portion coupled in flow communication with said first and said second plenum portions. 17. A gas turbine engine rotor assembly in accordance with claim 15 further comprising a first plenum portion, a second plenum portion, a first channel that extends between said dovetail lower surface and said cast-in plenum first portion, and a second channel that extends between said dovetail lower surface and said cast-in plenum second portion. 18. A gas turbine engine rotor assembly in accordance with claim 15 wherein said turbine rotor blade further comprises a first channel extending between said dovetail lower surface and a cast-in plenum first portion, and a second channel extending between said dovetail lower surface and a cast-in plenum second portion, said first and second channels extending along at least one of a platform upstream side and a platform downstream side. 19. A gas turbine engine rotor assembly in accordance with claim 15 wherein said turbine rotor blade further comprises a first channel extending between said dovetail lower surface and a cast-in plenum first portion, and a second channel extending between said dovetail lower surface and a cast-in plenum second portion, said first channel extends along at least one of a platform upstream side and a platform downstream side, said second channel extends along at least one of said platform upstream side and said platform downstream side opposite said first channel. 20. A gas turbine engine rotor assembly in accordance with claim 15 wherein said cast-in plenum further comprises a first plenum portion comprising a first side that includes a generally concave profile, a second plenum portion comprising a first side tat includes a generally convex profile, and a plurality of openings extending between said cast-in plenum and a platform outer surface, said plurality of openings sized to facilitate channeling a predetermined quantity of cooling air to said platform outer surface.