GAS TURBINE ENGINE COMPONENT HAVING TRANSVERSELY ANGLED IMPINGEMENT RIBS
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.
1 . A component for a gas turbine engine, comprising:
a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis;
at least one rib that extends between said first wall and said second wall, wherein said at least one rib extends along a rib axis that is transversely angled relative to said centerline axis; and
at least one impingement hole that extends through said at least one rib.
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 one of a blade outer air seal (BOAS) and a combustor liner.
4 . The component as recited in claim 1 , comprising a cooling circuit disposed within said body portion and including at least a first cavity and a second cavity in fluid communication with said first cavity.
5 . The component as recited in claim 1 , wherein said first wall is a suction side wall and said second wall is a pressure side wall.
6 . The component as recited in claim 1 , wherein said at least one impingement hole is oriented toward said first wall.
7 . The component as recited in claim 1 , wherein said at least one impingement hole is oriented toward said second wall.
8 . The component as recited in claim 1 , wherein said at least one rib includes a first impingement hole that is oriented toward said first wall and a second impingement hole that is oriented toward said second wall.
9 . The component as recited in claim 1 , comprising a second rib that extends between said first wall and said second wall, wherein said second rib extends along a second rib axis that is transversely angled at a different angle relative to said centerline axis than said rib axis of said at least one rib.
10 . The component as recited in claim 1 , wherein said at least one rib is positioned within a trailing edge portion of said body portion.
11 . The component as recited in claim 1 , wherein an interior surface of at least one of said first wall and said second wall includes a plurality of augmentation features.
12 . The component as recited in claim 11 , wherein said at least one impingement hole fluidly connects a first cavity and a second cavity of said component.
13 . A component for a gas turbine engine, comprising:
a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis;
at least one rib that extends between said first wall and said second wall, wherein a first portion of said at least one rib extends along a first rib axis that is angled at a first angle relative to said centerline axis and a second portion of said at least one rib extends along a second rib axis that is angled at a second angle relative to said centerline axis; and
at least one impingement hole that extends through said at least one rib.
14 . The component as recited in claim 13 , wherein said first portion and said second portion are located at different radial locations of said at least one rib.
15 . The component as recited in claim 13 , wherein said at least one impingement hole is oriented toward at least one of said first wall and said second wall.
16 . The component as recited in claim 13 , wherein said at least one rib includes impingement holes that are oriented toward both said first wall and said second wall.
17 . A casting system for manufacturing a gas turbine engine component, comprising:
a casting article that represents the dimensional negative of a cooling circuit of the gas turbine engine component, wherein the casting article includes at least one transversely angled opening that is configured to form at least one rib at a transverse angle relative to a centerline axis of the gas turbine engine component.
18 . The casting article as recited in claim 17 , wherein said casting article is a core.
19 . The casting article as recited in claim 17 , wherein said casting article is a shell.
20 . The casting article as recited in claim 17 , wherein said casting article includes at least one opening and at least one indent.