Gas turbine engine component cooling circuit
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.
1. A component for a gas turbine engine, comprising:
a body portion including an outer wall;
a cooling circuit disposed within said body portion and including at least a first cavity and a microcircuit provided in said outer wall and in fluid communication with said first cavity; and
a plunged hole that extends from said outer wall and that intersects at least a portion of said microcircuit such that a portion of said plunged hole extends past said microcircuit, such that said plunged hole extends to an innermost surface, said plunged hole and said microcircuit intersect at an intersection having an innermost point, and said innermost surface of said plunged hole is farther from an outer surface of said outer wall than said innermost point is from said outer surface; and
a bulged portion or a rib portion extending from said outer wall, wherein said plunged hole extends into said bulged portion or said rib portion.
2. The component as recited in claim 1 , wherein said body portion is an airfoil of one of a blade and a vane.
3. The component as recited in claim 1 , wherein said body portion is part of a blade outer air seal (BOAS).
4. The component as recited in claim 1 , comprising multiple rows of plunged holes that intersect said microcircuit.
5. The component as recited in claim 1 , wherein an outlet of said plunged hole is angled at an angle between 10 and 30 degrees relative to an exterior surface of said body portion.
6. The component as recited in claim 1 , wherein said plunged hole intersects one of a forward end portion and a trailing end portion of said microcircuit.
7. The component as recited in claim 1 , wherein said microcircuit extends from said first cavity toward one of a leading edge and a trailing edge of said body portion.
8. The component as recited in claim 1 , wherein said microcircuit includes a curved portion, and said plunged hole intersects said curved portion.
9. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication said combustor section;
a component disposed in at least one of said compressor section and said turbine section, wherein said component includes a body portion including an outer wall;
a cooling circuit disposed within said body portion and having a first cavity, a second cavity, and a microcircuit provided in said outer wall and fluidly connected to said cavity; and
a plunged hole that extends from said outer wall and that intersects at least a portion of said microcircuit such that a portion of said plunged hole extends past said microcircuit, such that said plunged hole extends to an innermost surface, said plunged hole and said microcircuit intersect at an intersection having an innermost point, and said innermost surface of said plunged hole is farther from an outer surface of said outer wall than said innermost point is from said outer surface, wherein said microcircuit extends from said first cavity, and said plunged hole is located proximate a second cavity.
10. The gas turbine engine as recited in claim 9 , wherein said plunged hole intersects with a forward end portion of said microcircuit.
11. The gas turbine engine as recited in claim 9 , comprising a second cavity adjacent to said cavity, wherein said second cavity includes a bulged portion and said plunged hole extends into said bulged portion.
12. The gas turbine engine as recited in claim 9 , wherein said microcircuit includes a curved portion and said plunged hole intersects said curved portion.
13. The gas turbine engine as recited in claim 9 , wherein an outlet of said plunged hole is positioned at an angle relative to an exterior surface of said body portion on a pressure side of said body portion.
14. A component for a gas turbine engine, comprising:
a body portion including a pressure side wall and a suction side wall;
a cooling circuit disposed within said body portion and including
a first cavity, a second cavity, and a third cavity, wherein said second cavity and said third cavity are separated by a rib extending from said pressure side wall and a suction side wall, and
a microcircuit provided in one of said pressure side wall and said suction side wall and in fluid communication with said first cavity; and
a plunged hole that extends from said outer wall and that intersects at least a portion of said microcircuit such that a portion of said plunged hole extends past said microcircuit and into said rib.
15. The component as recited in claim 14 , wherein said plunged hole extends to an innermost surface, said plunged hole and said microcircuit intersect at an intersection having an innermost point, and said innermost surface of said plunged hole is farther from an outer surface of said one of said pressure side wall and said suction side wall than said innermost point is from said outer surface.
16. The component as recited in claim 15 , wherein an outlet of said plunged hole is angled with said outer surface at an angle between 10 and 30 degrees.