Gas turbine engine component with impingement and diffusive cooling
A gas turbine engine component includes a gas path wall having a first surface and second surface and an impingement baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole extends through the gas path wall. The cooling hole continuously diverges from an inlet in the first surface to an outlet in the second surface such that cross-sectional area of the cooling hole increases continuously from the inlet to the outlet. A longitudinal ridge divides the cooling hole into lobes.
1. A gas turbine engine component comprising:
a gas path wall having a first surface and second surface;
an impingement baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall;
a cooling hole extending through the gas path wall, the cooling hole continuously diverging from an inlet in the first surface to an outlet in the second surface such that cross-sectional area of the cooling hole increases continuously from the inlet to the outlet; and
a longitudinal ridge dividing the cooling hole into lobes.
2. The component of claim 1 , and further comprising:
a cusp on the inlet, wherein the longitudinal ridge extends from the cusp along the cooling hole toward the outlet of the cooling hole.
3. The component of claim 1 , and further comprising:
a ridge terminus spaced along the cooling hole between the inlet and the outlet, wherein the longitudinal ridge terminates at the ridge terminus, and wherein the longitudinal ridge extends from the ridge terminus and along the cooling hole toward the outlet.
4. The component of claim 1 , wherein the cooling hole is one of a plurality of cooling holes, and wherein a total flow area of all of the impingement holes is less than a total flow area of all of the cooling holes.
5. The component of claim 1 , wherein the cooling hole is one of a plurality of cooling holes, wherein each of the impingement holes are paired with and positioned upstream of one of the cooling holes, and wherein a flow area of at least one of the impingement holes is less than a flow area of at least one of the cooling holes.
6. The component of claim 1 , wherein the impingement holes are substantially cylindrical.
7. The component of claim 1 , and further comprising:
bumps extending from the first surface toward the impingement baffle and substantially aligned with the impingement holes.
8. The component of claim 7 , wherein the bumps have a convex surface with a relatively steep slope in a longitudinally upstream direction and a relatively gradual slope in a longitudinally downstream direction.
9. The component of claim 1 , and further comprising:
a transition region extending from the longitudinal ridge to a trailing edge of the outlet, wherein the longitudinal ridge terminates at the transition region.
10. A combustor assembly comprising the component of claim 1 .
11. A liner assembly for a gas turbine engine, the liner assembly comprising:
an impingement baffle having impingement holes;
a liner wall having a first surface extending along the impingement baffle and a second surface extending opposite the first surface;
a cooling hole formed in the liner wall, the cooling hole diverging continuously from an inlet in the first surface to an outlet in the second surface; and
a longitudinal ridge dividing the cooling hole into lobes;
wherein the cooling hole is substantially diffusive from the inlet in the first surface of the liner wall to the outlet in the second surface of the liner wall.
12. The liner assembly of claim 11 , wherein the longitudinal ridge is a first longitudinal ridge, and further comprising:
a second longitudinal ridge; and
a third lobe, wherein the first and second longitudinal ridges divide the cooling hole into the first, second, and third lobes.
13. The liner assembly of claim 11 , wherein the longitudinal ridge extends toward the outlet from a ridge terminus spaced along the cooling hole between the inlet and the outlet.
14. The liner assembly of claim 11 , wherein the longitudinal ridge extends to a transition region of the cooling hole, the transition region extending from the longitudinal ridge to a trailing edge of the outlet.
15. The liner assembly of claim 11 , wherein the cooling hole is one of a plurality of cooling holes and wherein each of the impingement holes are paired with and positioned upstream of one of the cooling holes.
16. The liner assembly of claim 11 , wherein the impingement holes are substantially elongated slots.
17. The liner assembly of claim 11 , and further comprising:
bumps extending from the first surface toward the impingement baffle and substantially aligned with the impingement holes.
18. The liner assembly of claim 17 , wherein the bumps have a convex surface with a relatively steep slope in a longitudinally upstream direction and a relatively gradual slope in a longitudinally downstream direction.
19. A combustor comprising the liner assembly of claim 11 .
20. A gas turbine engine comprising the liner assembly of claim 11 .