Gas turbine engine airfoil cooling passage turbulator pedestal

1. A gas turbine engine component comprising:

a structure providing a cooling passage having a turbulator with a pedestal joining opposing first and second surfaces, the turbulator including first and second legs spaced apart from one another in a thickness direction and adjoining the pedestal, the first leg adjoining the second surface, and the second leg adjoining the first surface, and the pedestal extends in the thickness direction between the first and second surfaces, and the first and second legs do not fully extend between the first and second surfaces in the thickness direction, at least one of the first and second legs extend to a terminal end toward another pedestal, wherein the terminal end is disconnected from the other pedestal, wherein the structure includes first and second rows of pedestals, the first row of pedestals including the turbulator, wherein the turbulator is interleaved with the second row of pedestals, and the second row of pedestals arranged downstream from the first row of pedestals, wherein the first and second legs each include terminal ends that respectively provide first and second tips arranged downstream from the second row of pedestals.

2. The gas turbine engine component according to claim 1 , comprising a third row of pedestals arranged downstream from the second row of pedestals, the first and second tips arranged upstream from the third row of pedestals.

3. The gas turbine engine component according to claim 1 , wherein at least one of the first and second legs are airfoil-shaped.

4. The gas turbine engine component according to claim 1 , wherein at least one of the first and second legs are triangular-shaped.

5. The gas turbine engine component according to claim 1 , wherein the structure is an airfoil.

6. The gas turbine engine component according to claim 5 , wherein the first and second legs extend in a chordwise direction.

7. The gas turbine engine component according to claim 6 , wherein the turbulator is arranged in a trailing edge cooling passage.

8. The gas turbine engine component according to claim 1 , wherein first and second legs overlap in a radial direction.

9. The gas turbine engine component according to claim 1 , wherein the first and second legs are spaced apart from one another in a non-overlapping relationship in the radial direction.

10. The gas turbine engine component according to claim 1 , wherein the structure is one of a blade, vane, platform, blade outer air seal or combustor liner.

11. An airfoil for a gas turbine engine comprising:

an airfoil structure providing a cooling passage having a turbulator with a pedestal joining opposing first and second surfaces, the turbulator including first and second legs spaced apart from one another in a thickness direction and adjoining the pedestal, the first leg adjoining the second surface, the second leg adjoining the first surface, the pedestal extends in the thickness direction between the first and second surfaces, and the first and second legs extend in a chordwise direction, and the first and second legs do not fully extend between the first and second surfaces in the thickness direction, at least one of the first and second legs extend to a terminal end toward another pedestal, wherein the terminal end is disconnected from the other pedestal, wherein the structure includes first, second and third rows of pedestals, the first row of pedestals including the turbulator, and the second row of pedestals arranged downstream from the first row of pedestals, and the third row of pedestals arranged downstream from the second row of pedestals, the turbulator is interleaved with the second row of pedestals, the first and second legs each include terminal ends that respectively provide first and second tips arranged downstream from the second row of pedestals, the first and second tips arranged upstream from the third row of pedestals.

12. The airfoil according to claim 11 , wherein the airfoil is a turbine blade, and the turbulator is arranged in a trailing edge cooling passage.

13. The airfoil according to claim 11 , wherein first and second legs overlap in a radial direction.

14. The airfoil according to claim 11 , wherein the first and second legs are spaced apart from one another in a non-overlapping relationship in the radial direction.

15. A core for a producing a gas turbine engine component, comprising:

a core structure configured to provide a cooling passage, the core structure having an aperture corresponding to shape of a turbulator with a pedestal joining opposing first and second surfaces corresponding to opposing surfaces of the core structure, the aperture providing a turbulator shape configured to provide first and second legs spaced apart from one another in a thickness direction and adjoining the pedestal, the first leg adjoining the second surface, and the second leg adjoining the first surface, and the pedestal configured to extend in the thickness direction between the first and second surfaces, and the first and second legs do not fully extend between the first and second surfaces in the thickness direction, at least one of the first and second legs configured to extend to a terminal end toward another pedestal, wherein the terminal end is disconnected from the other pedestal, wherein the core structure configured to provide first and second rows of pedestals, the first row of pedestals including the turbulator, wherein the turbulator is interleaved with the second row of pedestals, and the second row of pedestals arranged downstream from the first row of pedestals, wherein the first and second legs configured to each include terminal ends that respectively provide first and second tips arranged downstream from the second row of pedestals.