Gaspath component including minicore plenums
A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.
1. A turbine engine component comprising:
a wall extending from a leading edge to a trailing edge, the wall including a hot side facing a gaspath when said gaspath component is in an installed state, and a cold side opposite said hot side;
at least one minicore cooling circuit disposed between said hot side and said cold side within said wall;
at least one cooling fluid inlet connecting the at least one minicore cooling circuit to a coolant source;
at least one film cooling hole connecting said at least one minicore cooling circuit to said hot side surface; and
the at least one minicore cooling circuit including an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the at least one minicore cooling circuit normal to the hot side surface, the edge plenum being a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge, and at least one of the at least one film cooling holes directly connects the edge plenum to the hot side surface.
2. The turbine engine component of claim 1 , further comprising a second edge plenum is-positioned at the at least one cooling fluid inlet.
3. The turbine engine component of claim 1 , wherein at least one of the at least one film cooling holes connects the edge plenum to the hot side.
4. The turbine engine component of claim 1 , wherein the edge plenum is a leading edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the at least one minicore cooling circuit normal to the hot side surface, the leading edge plenum being a portion of the at least one minicore cooling circuit most proximate to the leading edge.
5. The turbine engine component of claim 4 , wherein the leading edge plenum is configured to reverse a flow direction of a coolant passing through the at least one minicore circuit.
6. The turbine engine component of claim 5 , wherein the leading edge plenum is connected to the hot side surface by at least one of the at least one film cooling holes.
7. The turbine engine component of claim 4 , further comprising a trailing edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the at least one minicore cooling circuit normal to the hot side surface, the trailing edge plenum being a portion of the at least one minicore cooling circuit most proximate to the trailing edge.
8. The turbine engine component of claim 7 , wherein the thickness of the trailing edge plenum and the thickness of the leading edge plenum are the same.
9. The turbine engine component of claim 7 , wherein the thickness of the trailing edge plenum and the thickness of the leading edge plenum are different.
10. The turbine engine component of claim 1 , wherein a thickness of the wall normal to the hot side is approximately the same along a length of the at least one minicore cooling circuit.
11. The turbine engine component of claim 1 , wherein a thickness of the wall normal to the hot side at the edge plenum is larger than a thickness of the wall normal to the hot side along a remainder of the at least one minicore cooling circuit.
12. The turbine engine component of claim 1 , wherein the at least one minicore cooling circuit is an investment cast void, and wherein the film cooling holes are a product of a finishing process.
13. The turbine engine component of claim 12 , wherein the finishing process includes at least one of electrical discharge machining, laser drilling, and drilling.
14. The turbine engine component of claim 1 , wherein the at least one cooling fluid inlet is at least one impingement cooling fluid inlet.
15. The turbine engine component of claim 1 , wherein the at least one minicore cooling circuit includes at least one refractory metal core (RMC).
16. An investment casting core for a gaspath component comprising:
a body defining a three dimensional structure, wherein the three dimensional stricter is a negative space of at least one minicore cooling circuit, the at least one minicore cooling circuit having a leading edge plenum, wherein the leading edge plenum is thicker than at least a majority of the remainder of the at least one minicore cooling circuit.
17. The investment casting core of claim 16 , wherein the body further defines a negative space corresponding to a trailing edge plenum, the trailing edge plenum being thicker than at least a majority of the remainder of the at least one minicore cooling circuit.
18. The investment casting core of claim 16 , further comprising a plurality of posts extending outward from the negative space defining the leading edge plenum, each of the posts defining a negative space of an impingement cooling inlet.