Airfoil having dead-end tip flag cavity
Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.
1. An airfoil for a gas turbine engine, the airfoil comprising:
an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side;
a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity;
a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body, wherein the dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket arranged at the tip of the airfoil body, wherein the outer wall of the dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity, the down-pass serpentine cavity of the serpentine cavity, and the squealer pocket end at the same axial position in a direction between the leading edge and the trailing edge of the airfoil body.
2. The airfoil of claim 1 , further comprising at least one bleed hole arranged to fluidly connect the dead-end tip flag cavity and the serpentine cavity, the at least one bleed hole formed in the inner wall of the dead-end tip flag cavity.
3. The airfoil of claim 1 , further comprising at least one tip cooling hole formed within the outer wall and configured to enable fluid connection between the dead-end tip flag cavity and the squealer pocket.
4. The airfoil of claim 1 , further comprising a leading edge cavity extending in a direction from the platform to the tip and arranged along the leading edge of the airfoil body.
5. The airfoil of claim 4 , wherein the leading edge cavity and the dead-end tip flag cavity are fluidly connected.
6. The airfoil of claim 1 , wherein the trailing edge cavity includes an outer most trailing edge slot proximate to the tip and having a radial height, wherein a radial height of the dead-end tip flag cavity is equal to the radial height of the outer most trailing edge slot.
7. The airfoil of claim 1 , wherein the down-pass serpentine cavity of the serpentine cavity is defined in part by an aft down pass rib and wherein the dead-end wall of the dead-end cavity are aligned in a direction from the platform to the tip.
8. A gas turbine engine comprising:
a turbine section having a plurality of airfoils, wherein at least one airfoil comprises a blade having:
an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side;
a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity;
a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body, wherein the dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket arranged at the tip of the airfoil body, wherein the outer wall of the dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity, the down-pass serpentine cavity of the serpentine cavity, and the squealer pocket end at the same axial position in a direction between the leading edge and the trailing edge of the airfoil body.
9. The gas turbine engine of claim 8 , further comprising at least one bleed hole arranged to fluidly connect the dead-end tip flag cavity and the serpentine cavity, the at least one bleed hole formed in the inner wall of the dead-end tip flag cavity.
10. The gas turbine engine of claim 8 , further comprising a leading edge cavity extending in a direction from the platform to the tip and arranged along the leading edge of the airfoil body, wherein the leading edge cavity and the dead-end tip flag cavity are fluidly connected.
11. The gas turbine engine of claim 8 , wherein the trailing edge cavity includes an outer most trailing edge slot proximate to the tip and having a radial height, wherein a radial height of the dead-end tip flag cavity is equal to the radial height of the outer most trailing edge slot.
12. The gas turbine engine of claim 8 , wherein the down-pass serpentine cavity of the serpentine cavity is defined in part by an aft down pass rib and wherein the dead-end wall of the dead-end cavity are aligned in a direction from the platform to the tip.
13. A core assembly for the formation of an airfoil for a gas turbine engine, the core assembly comprising:
a serpentine cavity core configured to form a serpentine cavity in a formed airfoil, the serpentine cavity core having an up-pass serpentine cavity core, a down-pass serpentine cavity core, and a trailing edge cavity core; and
a dead-end tip flag cavity core positioned relative to the serpentine cavity core, the dead-end tip flag cavity core extending in a direction between a leading edge and a trailing edge of the formed airfoil, the dead-end tip flag cavity core arrange between the serpentine cavity core and a tip location of the formed airfoil, wherein the dead-end tip flag cavity core ends at a dead-end located at a position between the leading edge and the trailing edge of the formed airfoil,
wherein the dead-end tip flag cavity core is configured to form a dead-end tip flag cavity in the formed airfoil, wherein the formed dead-end tip flag cavity is defined by an outer wall, an inner wall, and the dead-end wall, with the outer wall and the inner wall extending in a direction between the leading edge and the trailing edge and the dead-end wall extending in a direction between the platform and the tip; and
a squealer pocket core arranged radially outward from the dead-end tip flag cavity core, wherein squealer pocket core is configured to form a squealer pocket and the outer wall of the formed dead-end tip flag cavity forms a pocket surface of the squealer pocket,
wherein the dead-end tip flag cavity core, the down-pass serpentine cavity of the serpentine cavity core, and the squealer pocket core end at the same axial position.
14. The core assembly of claim 13 , further comprising at least one stand-off connecting the dead-end tip flag cavity core to the serpentine cavity core, wherein the at least one stand-off forms bleed hole in the formed airfoil and arranged to fluidly connect the formed dead-end tip flag cavity and the formed serpentine cavity.