COOLING PASSAGES FOR GAS TURBINE ENGINE COMPONENT
A gas turbine engine component includes a wall having an inner surface and an outer surface. At least one non-rectangular slot extends through the outer wall surface and is in communication with a passage. The passages extend through the wall and include an inlet portion located at the inner surface and an outlet portion located at the outer surface. An intermediate portion fluidly connects the inlet portion and the outlet portion.
1 . A gas turbine engine component comprising:
a wall having an inner surface and an outer surface; and
at least one non-rectangular slot extending through the outer wall surface and in communication with a passage, the passages extending through the wall comprising:
an inlet portion located at the inner surface;
an outlet portion located at the outer surface; and
an intermediate portion fluidly connecting the inlet portion and the outlet portion.
2 . The gas turbine engine component of claim 1 , wherein slot includes an elongated trapezoidal shape.
3 . The gas turbine engine component of claim 1 , wherein the at least one non-rectangular slot includes a plurality of protrusions extending into the slot from at least one of a downstream side and an upstream side.
4 . The gas turbine engine component of claim 1 , wherein the at least one non-rectangular slot includes a serpentine profile.
5 . The gas turbine engine component of claim 1 , wherein the at least one non-rectangular slot includes a plurality of non-rectangular slots spaced radially from each other.
6 . The gas turbine engine component of claim 5 , wherein the plurality of non-rectangular slots are axially aligned on the outer surface of the wall and radially spaced from an adjacent one of the plurality of non-rectangular slots.
7 . The gas turbine engine component of claim 5 , wherein the intermediate portions of each of the adjacent plurality of non-rectangular slots are connected by an intermediate bridge portion.
8 . The gas turbine engine component of claim 1 , wherein at least one of the inlet portion, the outlet portion, and the intermediate portion includes a plurality of pedestals.
9 . The gas turbine engine component of claim 8 , further comprising a plurality of guide pedestals downstream of the plurality of pedestals and upstream of the slot.
10 . The gas turbine engine component of claim 1 , wherein the wall is located on at least one of a blade, a vane, a blade outer air seal, and a combustor liner.
11 . A wall of a component of a gas turbine engine subjected to a flow of high temperature gas, the wall comprising:
a wall having an inner surface and an outer surfaces; and
at least one non-rectangular slot extending through the outer wall surface and in communication with a passage, the passages extending through the wall comprising:
an inlet portion located at the inner surface;
an outlet portion located at the outer surface; and
an intermediate portion fluidly connecting the inlet portion and the outlet portion.
12 . The wall of claim 11 , wherein slot includes an elongated trapezoidal shape.
13 . The wall of claim 11 , wherein the non-rectangular slot includes a plurality of protrusions extending into the slot from at least one of a downstream side and an upstream side.
14 . The wall of claim 11 , wherein the non-rectangular slot includes a serpentine pattern.
15 . The wall of claim 11 , wherein the at least one non-rectangular slot includes a plurality of non-rectangular slots spaced radially from each other.
16 . The wall of claim 15 , wherein the intermediate portions of each of the adjacent plurality of non-rectangular slots are connected by an intermediate bridge portion.
17 . The wall of claim 11 , wherein at least one of the inlet portion, the outlet portion, and the intermediate portion includes a plurality of pedestals.
18 . The wall of claim 17 , further comprising a plurality of guide pedestals downstream of the plurality of pedestals and upstream of the slot.
19 . The wall of claim 11 , wherein the wall is located on at least one of a blade, a vane, a blade outer air seal, and a combustor liner.