Airfoil having forward flowing serpentine flow
Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from root to tip, a forward-flowing serpentine flow path formed within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body.
1. An airfoil for a gas turbine engine, the airfoil comprising:
an airfoil body having a leading edge and a trailing edge, a root region and a tip region, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region;
a forward-flowing serpentine flow path formed within the airfoil body, the forward-flowing serpentine flow path defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity;
a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region of the airfoil body; and
at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body,
wherein a cooling air flow is supplied into the forward-flowing serpentine flow path from a serpentine inlet at the first serpentine cavity, and the cooling air flow passes through the first serpentine cavity, the second serpentine cavity, the third serpentine cavity, into and through the tip flag cavity, and exits through the trailing edge of the airfoil body,
wherein at least one of the at least one shielding cavities is located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body.
2. The airfoil of claim 1 , further comprising:
a trailing edge cavity located aftward of the first serpentine cavity; and
a radially extending separating rib fluidly separating the trailing edge cavity from the first serpentine cavity.
3. The airfoil of claim 2 , wherein the trailing edge cavity is supplied with cooling air through a trailing edge inlet.
4. The airfoil of claim 2 , wherein the trailing edge cavity comprises one or more heat transfer augmentation features.
5. The airfoil of claim 1 , wherein the tip flag cavity comprises one or more heat transfer augmentation features.
6. The airfoil of claim 1 , wherein the at least one shielding cavity comprises a first shielding cavity and a second shielding cavity.
7. The airfoil of claim 1 , further comprising a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity, wherein a portion of the cooling air exits the hybrid trailing edge cavity at the trailing edge of the airfoil body and a portion of the cooling air flows from the first serpentine cavity into the second serpentine cavity.
8. The airfoil of claim 7 , further comprising a radially extending partitioning rib extending radially and separating the hybrid trailing edge cavity from the second serpentine cavity, wherein the hybrid trailing edge cavity is fluidly connected to the second serpentine cavity at a radially outward end of the radially extending partitioning rib.
9. The airfoil of claim 8 , further comprising a resupply connection fluidly connecting the hybrid trailing edge cavity to the second serpentine cavity at a radially inward end of the radially extending partitioning rib.
10. The airfoil of claim 1 , further comprising a platform wherein the root region of the airfoil body is integral with the platform.
11. The airfoil of claim 10 , wherein the serpentine inlet supplies serpentine cooling air through the platform.
12. The airfoil of claim 1 , wherein the at least one shielding cavity extends radially through the airfoil body from the root region to the tip region.
13. A gas turbine engine comprising:
a turbine section comprising a plurality airfoils, wherein at least one airfoil comprises:
an airfoil body having a leading edge and a trailing edge, a root region and a tip region, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region;
a forward-flowing serpentine flow path formed within the airfoil body, the forward-flowing serpentine flow path defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity;
a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region of the airfoil body; and
at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body,
wherein a cooling air flow is supplied into the forward-flowing serpentine flow path from a serpentine inlet at the first serpentine cavity, and the cooling air flow passes through the first serpentine cavity, the second serpentine cavity, the third serpentine cavity, into and through the tip flag cavity, and exits through the trailing edge of the airfoil body,
wherein at least one of the at least one shielding cavities is located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body.
14. The gas turbine engine of claim 13 , wherein the airfoil further comprises:
a trailing edge cavity located aftward of the first serpentine cavity; and
a radially extending separating rib fluidly separating the trailing edge cavity from the first serpentine cavity.
15. The gas turbine engine of claim 13 , wherein the at least one shielding cavity comprises a first shielding cavity and a second shielding cavity.
16. The gas turbine engine of claim 13 , wherein the airfoil further comprises:
a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity, wherein a portion of the cooling air exits the hybrid trailing edge cavity at the trailing edge of the airfoil body and a portion of the cooling air flows from the first serpentine cavity into the second serpentine cavity.
17. The gas turbine engine of claim 16 , wherein the airfoil further comprises:
a radially extending partitioning rib extending radially and separating the hybrid trailing edge cavity from the second serpentine cavity, wherein the hybrid trailing edge cavity is fluidly connected to the second serpentine cavity at a radially outward end of the radially extending partitioning rib.
18. The gas turbine engine of claim 17 , wherein the airfoil further comprises:
a resupply connection fluidly connecting the hybrid trailing edge cavity to the second serpentine cavity at a radially inward end of the radially extending partitioning rib.