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A main body is provided for a gas turbine engine comprising an outer structure, a first internal partition and a second internal partition. The outer structure and the first internal partition may define an entrance leg of a cooling circuit for receiving a cooling fluid. The second internal partitio

A main body is provided for a gas turbine engine comprising an outer structure, a first internal partition and a second internal partition. The outer structure and the first internal partition may define an entrance leg of a cooling circuit for receiving a cooling fluid. The second internal partition may include a metering slot. The outer structure, the first internal partition and the second internal partition may define an intermediate leg of the cooling circuit. The intermediate leg may communicate with the entrance leg. The second internal partition and the outer structure may define an exit leg of the cooling circuit. The metering slot meters cooling fluid as it passes from the intermediate leg into the exit leg.

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1. A blade for a gas turbine engine comprising: a main body comprising:an outer structure;a first internal partition, said outer structure and said first internal partition defining an entrance leg of a cooling circuit for receiving a cooling fluid; anda second internal partition including a meterin

1. A blade for a gas turbine engine comprising: a main body comprising:an outer structure;a first internal partition, said outer structure and said first internal partition defining an entrance leg of a cooling circuit for receiving a cooling fluid; anda second internal partition including a metering slot extending to a lowermost portion of said outer structure, said first internal partition being located nearer to a leading edge than said second internal partition;wherein said outer structure, said first internal partition and said second internal partition defining an intermediate leg of said cooling circuit, said intermediate leg communicating with said entrance leg, and said second internal partition and said outer structure defining an exit leg of said cooling circuit that includes a substantial portion that is located adjacent to said intermediate leg, said metering slot formed between said intermediate leg and said exit leg and metering cooling fluid as it passes from said intermediate leg into said exit leg such that a pressure of the cooling fluid in said intermediate leg is greater than a pressure of the cooling fluid in said exit leg. 2. The blade as set out in claim 1, wherein said outer structure defines at least portions of an attachment, a platform and an airfoil, said airfoil comprising a root section, a tip, said leading edge, a trailing edge, a pressure side and a suction side. 3. The blade as set out in claim 2, wherein said outer structure comprises: an airfoil outer wall defining said root section, said leading edge, said trailing edge, said pressure side and said suction side of said airfoil;said airfoil tip; andan intermediate wall extending from said airfoil root section to said airfoil tip and defining with a leading edge section of said airfoil outer wall an impingement cavity, said intermediate wall including a plurality of bores through which cooling fluid passes under pressure from said entrance leg of said cooling circuit into said impingement cavity so as to impinge upon an inner surface of said leading edge section of said outer wall. 4. The blade as set out in claim 3, wherein said leading edge section of said airfoil outer wall comprises a plurality of bores which extend from said inner surface of said leading edge section to an outer surface of said leading edge section, said bores in said leading edge section communicate with said impingement cavity. 5. The blade as set out in claim 3, wherein said first internal partition extends from a lower surface of said attachment, through said attachment and said platform, into and through a substantial length of said airfoil outer wall and terminating near said airfoil tip. 6. The blade as set out in claim 5, wherein said second internal partition extends from said airfoil tip, through said airfoil outer wall, said platform and said attachment and terminates at said attachment lower surface. 7. The blade as set out in claim 3, wherein a trailing edge section of said airfoil outer wall comprises a plurality of bores which extend from an inner surface of said trailing edge section to an outer surface of said trailing edge section. 8. The blade as set out in claim 3, further comprising a first rib plate extending from near said root section of said airfoil to near said airfoil tip and further extending between said suction and pressure sides of said airfoil, said first rib plate including a plurality of bores extending therethrough. 9. The blade as set out in claim 8, further comprising a second rib plate extending from near said root section of said airfoil to near said airfoil tip and further extending between said suction and pressure sides of said airfoil, said second rib plate including a plurality of bores extending therethrough, wherein cooling fluid passing through said bores in said first rib plate impinge upon said second rib plate. 10. The blade as set out in claim 2, further comprising a plate structure for allowing the cooling fluid to effect a sequence of impingement cooling prior to passing through trailing edge section bores. 11. A blade for a gas turbine engine comprising: a main body comprising:an outer structure defining at least portions of an attachment;a first internal partition, said outer structure and said first internal partition defining an entrance leg of a cooling circuit for receiving a cooling fluid; anda second internal partition including a metering slot having a radial length generally corresponding to a radial length of said attachment and extending to a lowermost portion of said outer structure, said first internal partition being located nearer to a leading edge than said second internal partition;wherein said outer structure, said first internal partition and said second internal partition defining an intermediate leg of said cooling circuit, and said second internal partition and said outer structure defining an exit leg of said cooling circuit that includes a substantial portion that is located adjacent to said intermediate leg, said metering slot formed between said intermediate leg and said exit leg and defining a mechanism for causing a pressure of the cooling fluid in said entrance and intermediate legs to be greater than a pressure of the cooling fluid in said exit leg. 12. The blade as set out in claim 11, wherein said outer structure further defines at least portions of a platform and an airfoil, said airfoil comprising a root section, a tip, said leading edge, a trailing edge, a pressure side and a suction side, and said second internal partition extends from a lower surface of said attachment to said tip. 13. The blade as set out in claim 12, wherein said outer structure comprises: an airfoil outer wall defining said root section, said leading edge, said trailing edge, said pressure side and said suction side of said airfoil;said airfoil tip; andan intermediate wall extending from said airfoil root section to said airfoil tip and defining with a leading edge section of said airfoil outer wall an impingement cavity, said intermediate wall including a plurality of bores through which cooling fluid passes under pressure from said entrance leg of said cooling circuit into said impingement cavity so as to impinge upon an inner surface of said leading edge section of said outer wall. 14. The blade as set out in claim 13, wherein said leading edge section of said airfoil outer wall comprises a plurality of bores which extend from said inner surface of said leading edge section to an outer surface of said leading edge section, said bores in said leading edge section communicate with said impingement cavity. 15. The blade as set out in claim 13, wherein said first internal partition extends from said lower surface of said attachment, through said attachment and said platform, into and through a substantial length of said airfoil outer wall and terminating near said airfoil tip. 16. The blade as set out in claim 15, wherein said second internal partition extends from said airfoil tip, through said airfoil outer wall, said platform and said attachment and terminates at said attachment lower surface. 17. The blade as set out in claim 13, wherein a trailing edge section of said airfoil outer wall comprises a plurality of bores which extend from an inner surface of said trailing edge section to an outer surface of said trailing edge section. 18. The blade as set out in claim 12, further comprising a plate structure for allowing the cooling fluid to effect a sequence of impingement cooling prior to passing through trailing edge section bores. 19. A main body for a gas turbine engine comprising: an outer structure defining at least portions of an attachment;a first internal partition, said outer structure and said first internal partition defining an entrance leg of a cooling circuit for receiving a cooling fluid; anda second internal partition including a metering slot extending through at least a substantial portion of said attachment and including a radially innermost portion near a radially innermost portion of said attachment, said first internal partition being located nearer to a leading edge than said second internal partition;wherein said outer structure, said first internal partition and said second internal partition defining an intermediate leg of said cooling circuit, said intermediate leg communicating with said entrance leg, and said second internal partition and said outer structure defining an exit leg of said cooling circuit that includes a substantial portion that is located adjacent to said intermediate leg, said metering slot formed between said intermediate leg and said exit leg extending to a lowermost portion of said outer structure, and metering cooling fluid as it passes from said intermediate leg into said exit leg such that the cooling fluid after passing into said exit leg effects a sequence of impingement cooling in a plate structure prior to passing through an airfoil trailing edge section of said outer structure. 20. The main body as set out in claim 19, wherein said outer structure further defines at least portions of an airfoil comprising said leading edge, said trailing edge, a pressure side and a suction side.