Hourglass airfoil cooling configuration
In one exemplary embodiment, an airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls also extend in a radial direction to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction walls. The cooling passage has a first width in the chord-wise direction near the suction side wall. A second width is in the chord-wise direction near the pressure side wall. A third width is between the pressure and suction side walls. The third width is smaller than the first and second widths.
1. An airfoil, comprising:
pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls also extending in a radial direction to provide an exterior airfoil surface; and
a first cooling passage, a second cooling passage, and a third cooling passage arranged between the pressure and suction walls, the first and third cooling passages arranged on either side of the second cooling passage, the first and third cooling passages each having a first width in the chord-wise direction near the suction side wall, a second width in the chord-wise direction near the pressure side wall, and a third width between the pressure and suction side walls, the third width being smaller than the first and second widths, and wherein the second cooling passage has a kite shape.
2. The airfoil of claim 1 , wherein a plurality of apertures connect the second cooling passage with the fir cooling passage.
3. The airfoil of claim 1 , wherein the first and third cooling passages have an hourglass shape.
4. The airfoil of claim 1 , wherein the third width of the first cooling passage is between 0.002 and 0.100 inches (0.0508-2.540 mm).
5. The airfoil of claim 1 , wherein the first width defines a suction side cavity, the second width defines a pressure side cavity, and the third width defines a passage between the pressure and suction side cavities of each of the first and third cooling passages.
6. The airfoil of claim 5 , wherein the pressure and suction side cavities are defined by a first internal wall and a second internal wall, each of the first and second internal walls having a bent portion.
7. The airfoil of claim 6 , wherein each of the first and second internal walls has a constant thickness between the pressure and suction walls.
8. The airfoil of claim 6 , wherein each of the first and second internal walls has a first portion and a second portion arranged at an angle relative to the first portion, and the angle is greater than 90°.
9. The airfoil of claim 1 , wherein the first, second, and third cooling passages are in communication with one another in a serpentine cooling configuration.
10. The airfoil of claim 1 , each of the first, second, and third cooling passages are configured to receive air from a source and to direct the air flow radially.
11. The airfoil of claim 1 , wherein a fourth cooling passage having a kite shape is arranged adjacent the third cooling passage and a fifth cooling passage having an hourglass shape is arranged adjacent the fourth cooling passage.
12. The airfoil of claim 11 , wherein the first cooling passage, second cooling passage, third cooling passage, fourth cooling passage, and fifth cooling passage are in communication with one another in a serpentine cooling configuration.
13. A gas turbine engine, comprising:
a combustor section arranged fluidly between compressor and turbine sections;
an airfoil arranged in the turbine section, the airfoil having pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls also extending in a radial direction to provide an exterior airfoil surface, and a first cooling passage, a second cooling passage, and a third cooling passage arranged between the pressure and suction walls, the first and third cooling passages arranged on either side of the second cooling passage, the first and third cooling passages each having a first width in the chord-wise direction near the suction side wall, a second width in the chord-wise direction near the pressure side wall, and a third width between the pressure and suction side walls, the third width being smaller than the first and second widths, and wherein the second cooling passage has a kite shape.
14. The gas turbine engine of claim 13 , wherein a plurality of apertures connect the second cooling passage with the first cooling passage.
15. The gas turbine engine of claim 13 , wherein the first and third cooling passages have an hourglass shape.
16. The gas turbine engine of claim 13 , wherein the third width of the first cooling passage is between 0.002 and 0.100 inches (0.0508-2.540 mm).
17. The gas turbine engine of claim 13 , wherein the first width defines a suction side cavity, the second width defines a pressure side cavity, and the third width defines a passage between the pressure and suction side cavities of each of the first and third cooling passages.
18. The gas turbine engine of claim 17 , wherein the pressure and suction side cavities are defined by a first internal wall and a second internal wall, each of the first and second internal walls having a bent portion.
19. The gas turbine engine of claim 13 , wherein the first, second, and third cooling passages are in communication with one another in a serpentine cooling configuration.
20. The gas turbine of claim 13 , wherein the first, second, and third cooling passages are configured to receive air from a source and to direct the air flow radially.