Radially diffused tip flag
An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip surface, and a rib. The first wall radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge. The second wall radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge. The third wall radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge. The tip surface circumferentially extends between the second wall and the third wall. The rib is radially spaced apart from the tip surface and circumferentially extends between the first wall and the third wall.
1. An airfoil for a gas turbine engine, comprising:
an airfoil body including:
a first wall that radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge;
a second wall that radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge;
a third wall that radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge;
a tip surface that circumferentially extends between the second wall and the third wall;
a rib that is radially spaced apart from the tip surface;
a tip flag cavity defined between the rib, the tip surface, the first wall, and the third wall, wherein the rib is disposed in a non-parallel relationship with the tip surface and the rib is disposed progressively further away from the tip surface as it extends in a direction from the leading edge towards the trailing edge.
2. The airfoil of claim 1 , wherein the tip flag cavity is spaced apart from the leading edge.
3. The airfoil of claim 1 , wherein the rib defines a radial diffusion angle of the tip flag cavity.
4. The airfoil of claim 3 , further comprising
a pocket surface that is axially spaced apart from the tip surface.
5. The airfoil of claim 4 , wherein the pocket surface is disposed parallel to but not coplanar with the tip surface.
6. The airfoil of claim 4 , wherein the airfoil body defines a radial flow cavity that is disposed proximate the leading edge and radially extends from the root region towards the tip region.
7. The airfoil of claim 6 , wherein the radial flow cavity is fluidly connected to the tip flag cavity.
8. An airfoil for a gas turbine engine, comprising:
an airfoil body defining a leading edge, a trailing edge, a tip region, and a root region, the airfoil body having:
a first wall that radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge;
a second wall that is circumferentially spaced apart from the first wall and radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge;
a third wall that is circumferentially spaced apart from the second wall and radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge;
a tip shelf disposed proximate the tip region;
a rib that is radially spaced apart from the tip shelf; and
a tip flag cavity that is defined between the rib, the tip shelf, the first wall, and the third wall, wherein the rib is disposed in a non-parallel relationship with the tip shelf such that the rib defines a radial diffusion angle of the tip flag cavity.
9. The airfoil of claim 8 , wherein the airfoil body defines a radial flow cavity that is disposed proximate the leading edge and is operatively connected to the tip flag cavity.
10. The airfoil of claim 9 , wherein the airfoil body defines a first pressure side hybrid skin core cavity that radially extends from the tip region towards the root region and is located between the first wall and the second wall and is spaced apart from the leading edge.
11. The airfoil of claim 10 , wherein the airfoil body defines a leading edge hybrid skin core cavity that is circumferentially spaced apart from the first pressure side hybrid skin core cavity and is disposed proximate the leading edge.
12. The airfoil of claim 11 , wherein the airfoil body defines a suction side hybrid skin core cavity that is circumferentially spaced apart from the leading edge hybrid skin core cavity and is spaced apart from the leading edge.
13. The airfoil of claim 12 , wherein the first pressure side hybrid skin core cavity, the leading edge hybrid skin core cavity, and the suction side hybrid skin core cavity are separated from the radial flow cavity by an internal partition wall.