Gas turbine engine component with angled aperture impingement

Abstract

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. At least one rib extends between the first wall and the second wall and at least one aperture extends through the at least one rib. The at least one aperture is angled relative to a radial axis of the at least one rib.

What is claimed is: 
     
         1 . A component for a gas turbine engine, comprising:
 a body portion that includes a first wall spaced apart from a second wall;   at least one rib that extends between said first wall and said second wall; and   at least one aperture that extends through said at least one rib, wherein said at least one aperture is angled relative to a radial axis of 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 2 , wherein said first wall is a suction side wall and said second wall is a pressure side wall of said airfoil. 
     
     
         4 . The component as recited in  claim 1 , wherein said body portion is part of a blade outer air seal (BOAS). 
     
     
         5 . 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. 
     
     
         6 . The component as recited in  claim 1 , wherein said at least one aperture includes an aspect ratio of between 1:1 and 5:1. 
     
     
         7 . The component as recited in  claim 1 , wherein said at least one aperture is angled in a clockwise direction from a horizontal axis that intersects said radial axis. 
     
     
         8 . The component as recited in  claim 1 , wherein said at least one aperture is angled in a counterclockwise direction from a horizontal axis that intersects said radial axis. 
     
     
         9 . The component as recited in  claim 1 , comprising a first portion of slots oriented at a first angle relative to said radial axis and a second portion of slots oriented at a second, different angle relative to said radial axis. 
     
     
         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 a width of said at least one aperture is at least 50% of a width of said at least one rib. 
     
     
         12 . The component as recited in  claim 1 , wherein said at least one aperture is angled at a non-perpendicular angle relative to said radial axis. 
     
     
         13 . 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 having a first wall spaced apart from a second wall;   at least one rib that extends between said first wall and said second wall; and   at least one aperture that extends through said at least one rib, wherein said at least one aperture is angled relative to a radial axis of said at least one rib.   
     
     
         14 . The gas turbine engine as recited in  claim 13 , wherein said at least one aperture includes an aspect ratio of between 1:1 and 5:1. 
     
     
         15 . The gas turbine engine as recited in  claim 13 , wherein said at least one aperture is angled at a non-perpendicular angle relative to said radial axis. 
     
     
         16 . The gas turbine engine as recited in  claim 13 , comprising a first portion of slots oriented at a first angle relative to said radial axis and a second portion of slots oriented at a second, different angle relative to said radial axis. 
     
     
         17 . A method of providing a component for a gas turbine engine, comprising the steps of:
 communicating cooling airflow into a cooling circuit disposed inside of the component, wherein the cooling circuit includes a first cavity, a second cavity and a rib between the first cavity and the second cavity;   communicating the cooling airflow from the first cavity into the second cavity through an aperture that extends through the rib, wherein the aperture is angled relative to a radial axis of the rib.   
     
     
         18 . The method as recited in  claim 17 , wherein the cooling airflow that is communicated through the aperture impinges upon an interior surface of a wall of the component. 
     
     
         19 . The method as recited in  claim 17 , wherein the rib includes a first portion of slots oriented at a first angle relative to the radial axis and a second portion of slots oriented at a second, different angle relative to the radial axis such that the cooling airflow that is communicated through the first portion of slots impinges on an interior surface of a first wall and the cooling airflow that is communicated through the second portion of slots impinges upon an interior surface of a second wall of the component.