Cooling circuit flow path for a turbine section airfoil
A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
1. A cooled airfoil within a gas turbine engine comprising:
an airfoil which defines a forward cavity and a leading edge cavity between a pressure side wall and a suction side wall;
a rib between said pressure side wall and said suction side wall to separate said forward cavity and said leading edge cavity, said forward cavity in communication with a cooling circuit flow path;
an opening through said rib, said opening offset within said forward cavity and said leading edge cavity relative a longitudinal axis of said airfoil toward said pressure side wall;
a multiple of turbulators within said leading edge cavity on said pressure side wall; and
a multiple of showerhead holes through a leading edge of said leading edge cavity, wherein said multiple of turbulators include angled trip strips, and wherein one of said multiple of showerhead holes extends through one of said angled trip strips.
2. The airfoil as recited in claim 1 , wherein said multiple of turbulators are opposite a multiple of gill holes located through said suction side wall within said leading edge cavity.
3. The airfoil as recited in claim 1 , wherein said airfoil is rotationally stationary.
4. The airfoil as recited in claim 3 , wherein said rotationally stationary airfoil is a turbine vane.
5. The airfoil as recited in claim 1 , further comprising a multiple of gill holes through a suction side wall within said leading edge cavity.
6. The airfoil as recited in claim 1 , wherein a portion of said one of said angled trip strips defines a portion of an outer periphery of said one of said multiple of showerhead holes.
7. The airfoil as recited in claim 1 , wherein said multiple of angled trip strips extend within said leading edge cavity on said pressure side wall without extending to said suction side wall.
8. The airfoil as recited in claim 1 , wherein a longitudinal axis bifurcates said leading edge cavity, said angled trip strips being non-parallel to said longitudinal axis.
9. A turbine vane within a gas turbine engine comprising:
an airfoil which defines a forward cavity and a leading edge cavity between a pressure side wall and a suction side wall;
a rib between said pressure side wall and said suction side wall to separate said forward cavity and said leading edge cavity, said forward cavity in communication with a cooling circuit flow path;
a multiple of gill holes through said suction side wall within said leading edge cavity;
an opening through said rib, said opening offset within said forward cavity and said leading edge cavity toward said pressure side wall opposite said multiple of gill holes; and
a multiple of turbulators on said pressure side wall opposite said multiple of gill holes;
a multiple of showerhead holes through a leading edge of said leading edge cavity, wherein said multiple of turbulators include angled trip strips, and wherein one of said multiple of showerhead holes extends through one of said angled trip strips.
10. The turbine vane as recited in claim 9 , wherein said airfoil is rotationally stationary.
11. The turbine vane as recited in claim 10 , wherein said rotationally stationary airfoil is a turbine vane.
12. The turbine vane as recited in claim 9 , wherein a portion of said one of said angled trip strips defines a portion of an outer periphery of said one of said multiple of showerhead holes.