Gas turbine engine component with impingement and lobed cooling hole
A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole is formed in the gas path wall and extends from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface. A longitudinal ridge extends along the cooling hole between the transition and the outlet. The longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes.
1. A gas turbine engine component comprising:
a gas path wall having a first and second opposing surfaces and defining a cooling hole, the cooling hole extending from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface;
a baffle positioned along the gas path wall, the baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall;
a first longitudinal ridge extending along the cooling hole between the transition and the outlet; and
a second longitudinal ridge, wherein the first and second longitudinal ridges divide the cooling hole into first, second, and third lobes.
2. The component of claim 1 , wherein the outlet has an arcuate upstream wall extending downstream to a substantially straight trailing edge.
3. The component of claim 1 , 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.
4. The component of claim 1 , wherein the impingement holes are substantially cylindrical.
5. The component of claim 1 , and further comprising:
bumps extending from the first surface toward the baffle and substantially aligned with the impingement holes.
6. The component of claim 5 , 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.
7. 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.
8. A combustor assembly comprising the component of claim 1 .
9. A gas turbine engine component comprising:
a gas path wall having a first and second opposing surfaces and defining a cooling hole, the cooling hole extending from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface;
a baffle positioned along the gas path wall, the baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall;
a longitudinal ridge extending along the cooling hole from the transition to the outlet, the longitudinal ridge dividing the diffusing section of the cooling hole into first and second lobes; and
a cusp on the inlet, wherein the longitudinal ridge extends through the transition and along the metering section of the cooling hole to the cusp.
10. The component of claim 9 , wherein the outlet has an arcuate upstream wall extending downstream to a substantially straight trailing edge.
11. The component of claim 9 , wherein the impingement holes are substantially cylindrical.
12. 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 and defining a cooling hole, the cooling hole extending from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface;
a first longitudinal ridge extending between the transition and the outlet; and
a second longitudinal ridge, wherein the first and second longitudinal ridges divide the cooling hole into the first, second, and third lobes.
13. The liner assembly of claim 12 , wherein cross sectional area of the cooling hole does not increase from the inlet through the metering section to the transition.
14. The liner assembly of claim 13 , wherein cross sectional area of the cooling hole increases from the transition through the diffusing section to the outlet.
15. The liner assembly of claim 12 , 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 12 , wherein the impingement holes are substantially elongated slots.
17. The liner assembly of claim 12 , 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 gas turbine engine component comprising the liner assembly of claim 12 .
20. A liner assembly for a gas turbine engine 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 and defining a cooling hole, the cooling hole extending from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface;
a longitudinal ridge extending from the transition to the outlet, wherein the longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes; and
a cusp on the inlet, wherein the longitudinal ridge extends through the transition and along the metering section of the cooling hole to the cusp.