Dirt separator for internally cooled components

1. A gas turbine engine internally cooled component airfoil, comprising:

a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from a proximate end to a distal end; and

a cooling system comprising at least one or more passages bounded in part by the peripheral wall, where at least a first of the one or more passages includes a first passage pressure side surface that includes an interior protrusion comprising a first sloped surface extending to a peak of the interior protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface, where the slope of the second sloped surface is greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion to vent the first of the one or more passages to the pressure side surface;

where the first and second sloped surfaces intersect to form a rounded edge; and

where the slope of the first sloped surface and the slope of the second sloped surface are selected to dirt particles within the first passage are routed away from the first cooling hole.

2. The gas turbine engine internally cooled component of claim 1 further comprising a debris passage in a radial tip of the internally cooled airfoil and in fluid communication with the first passage to allow debris to pass from the first passage through the debris passage.

3. The gas turbine engine internally cooled component of claim 1 , where the first cooling hole has a circular cross section, the proximate end is adjacent to an airfoil root and the distal end is adjacent to an airfoil tip.

4. The gas turbine engine internally cooled component of claim 3 , where the interior protrusion has substantially a bulbous shape.

5. The gas turbine engine internally cooled component of claim 3 , where the first passage and a second passage of the one or more passages are chordwisely adjacent and radially extending.

6. The gas turbine engine internally cooled component of claim 5 , where the first and second passages are interconnected to form a cooling serpentine.

7. A gas turbine engine internally cooled airfoil, comprising:

a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip;

a cooling system comprising at least two passages bounded in part by the peripheral wall, chordwisely adjacent and radially extending from the airfoil root to the airfoil tip, where each of the at least two passages includes a passage pressure side surface that includes an interior air/dirt separating protrusion comprising a first sloped surface extending to a peak of the interior air/dirt separating protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface, where the slope of the second sloped surface is greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the air/dirt separating interior protrusion to vent the respective first or second passage to the pressure side surface; and

an airfoil tip surface that substantially seals each of the least two passages at a tip region of the airfoil, where the airfoil tip surface comprises a radially extending debris hole that allows debris particles to exit the airfoil from each of the at least two passages;

where the first and second sloped surfaces intersect to form a rounded edge and slope of the first sloped surface and slope of the second sloped surface are selected so dirt particles within the first passage are routed away from the first cooling hole.

8. The internally cooled airfoil of claim 7 , where the first cooling hole has a circular cross section and the radially extending debris hole also has a circular cross section.

9. The internally cooled airfoil of claim 8 , where the interior protrusion has substantially a bulbous shape.

10. The internally cooled airfoil of claim 8 , where the first and second passages are interconnected to form a cooling serpentine.

11. A gas turbine engine internally cooled component, comprising:

a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip; and

a cooling system comprising at least two passages bounded in part by the peripheral wall, where at least a first of the at least two passages includes a first passage pressure side surface that includes an interior protrusion comprising a first sloped surface extending to a peak of the interior protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface, where the slope of the second sloped surface is greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion to vent the first of the at least two passages to the pressure side surface;

where the first and second sloped surfaces intersect to form a rounded edge, and slope of the first sloped surface and slope of the second sloped surface are selected so dirt particles within the first passage are routed away from the first cooling hole.

12. The gas turbine engine internally cooled component of claim 11 further comprising a debris passage in a radial tip of the internally cooled component and in fluid communication with the first passage to allow debris to pass from the first passage through the debris passage.

13. The gas turbine engine internally cooled component of claim 12 , where the first cooling hole has a circular cross section.

14. The gas turbine engine internally cooled component of claim 13 , where the interior protrusion has substantially a bulbous shape.

15. The gas turbine engine internally cooled component of claim 14 , where the at least two passages are chordwisely adjacent and radially extending.

16. The gas turbine engine internally cooled component of claim 15 , where the at least two passages are interconnected to form a cooling serpentine.