The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively d
The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.
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1. An airfoil for a gas turbine rotor blade, comprising: a pressure side wall;a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion, the pressure side wall and the suction side wall collectively defining an internal cavity within the airfoil; a
1. An airfoil for a gas turbine rotor blade, comprising: a pressure side wall;a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion, the pressure side wall and the suction side wall collectively defining an internal cavity within the airfoil; anda plurality of pins disposed within the internal cavity;wherein the trailing edge portion defines a first cooling passage comprising a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length, the first length being greater than the second length, and a third cooling passage comprising a third inlet spaced apart from a third outlet by a third length, the third length being less than the first and second lengths, the third cooling passage being positioned radially between the first and second cooling passages, and wherein at least one of the first cooling passage, second cooling passage, and third cooling passage is parallel to another one of the first cooling passage, second cooling passage, and third cooling passage. 2. The airfoil of claim 1, wherein a first diameter of the first cooling passage is less than a second diameter of the second cooling passage. 3. The airfoil of claim 1, wherein the first inlet of the first cooling passage is spaced apart along a camber line from the second inlet of the second cooling passage. 4. The airfoil of claim 3, wherein the second inlet of the second cooling passage is positioned between the first inlet of the first cooling passage and the first outlet of the first cooling passage along the camber line. 5. The airfoil of claim 1, wherein the trailing edge portion defines the third cooling passage comprising the third inlet spaced apart from the third outlet, and wherein a third diameter of the third cooling passage is less than the second diameter and greater than the first diameter. 6. The airfoil of claim 5, wherein the first cooling passage comprises a plurality of first cooling passages, the second cooling passage comprises a plurality of second cooling passages, and the third cooling passage comprises a plurality of third cooling passages. 7. The airfoil of claim 5, wherein the first cooling passage is positioned radially outwardly from the third cooling passage, and wherein the third cooling passage is positioned radially outwardly from the second cooling passage. 8. The airfoil of claim 1, wherein the plurality of pins comprises: a first subset of the plurality of pins extending from an inner surface of the pressure side wall to an inner surface of the suction side wall; anda second subset of the plurality of pins extending from the inner surface of the pressure side wall or the inner surface of the suction side wall to a position within the internal cavity spaced apart from the inner surface of the pressure side wall and the inner surface of the suction side wall. 9. The airfoil of claim 8, wherein at least one pin of the second subset of the plurality of pins extends from the inner surface of the pressure side wall or the inner surface of the suction side wall to a position on a camber line of the airfoil. 10. The airfoil of claim 8, wherein a first portion of the second subset of the plurality of pins couples to the inner surface of the pressure side wall and a second portion of the second subset of the plurality of pins couples to the inner surface of the suction side wall. 11. The airfoil of claim 10, wherein the first portion of the second subset of the plurality of pins comprises a first pin and the second portion of the second subset of the plurality of pins comprises a second pin, and wherein the first pin is coaxial with the second pin. 12. A gas turbine engine, comprising: a compressor section;a combustion section; anda turbine section comprising one or more rotor blades, each rotor blade comprising: a platform comprising a radially inner surface and a radially outer surface;a connection portion extending radially inwardly from the radially inner surface of the platform; andan airfoil extending radially outwardly from the radially outer surface of the platform to an airfoil tip, the airfoil comprising: a pressure side wall;a suction side wall connected to the pressure side wall at a leading edge and a trailing edge, the pressure side wall and the suction side wall collectively defining an internal cavity within the airfoil; anda plurality of pins disposed within the internal cavity;wherein the trailing edge defines a first cooling passage comprising a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length, the first length being greater than the second length, and a third cooling passage comprising a third inlet spaced apart from a third outlet by a third length, the third length being less than the first and second lengths, the third cooling passage being positioned radially between the first and second cooling passage, and wherein at least one of the first cooling passage, second cooling passage, and third cooling passage is parallel to another one of the first cooling passage, second cooling passage, and third cooling passage. 13. The gas turbine engine of claim 12, wherein a first diameter of the first cooling passage is less than a second diameter of the second cooling passage. 14. The gas turbine engine of claim 12, wherein the trailing edge defines the third cooling passage comprising the third inlet spaced apart from the third outlet, and wherein a third diameter of the third cooling passage is less than the second diameter and greater than the first diameter. 15. The gas turbine engine of claim 12, wherein the plurality of pins comprises: a first subset of the plurality of pins extending from an inner surface of the pressure side wall to an inner surface of the suction side wall; anda second subset of the plurality of pins extending from the inner surface of the pressure side wall or the inner surface of the suction side wall to a position within the internal cavity spaced apart from the inner surface of the pressure side wall and the inner surface of the suction side wall. 16. The gas turbine engine of claim 15, wherein at least one pin of the second subset of the plurality of pins extends from the inner surface of the pressure side wall or the inner surface of the suction side wall to a position on a camber line of the airfoil. 17. The gas turbine engine of claim 15, wherein a first portion of the second subset of the plurality of pins couples to the inner surface of the pressure side wall and a second portion of the second subset of the plurality of pins couples to the inner surface of the suction side wall.
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