Gas turbine engine component with rib support

1. A component, comprising:

an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending radially from a base to a tip;

a plenum defined inside said airfoil, and said plenum is positioned in said tip;

a first cooling cavity merging into said plenum;

a second cooling cavity merging into said plenum; and

a rib that extends from said first sidewall at least partially into said plenum to separate said first cooling cavity from said second cooling cavity, wherein said rib extends radially between opposing sides of said plenum such that said first cooling cavity and said second cooling cavity extend along said first sidewall on opposed sides of said rib, said rib extends transversely between said opposing sides, one of said opposite sides defining a floor and another one of said opposing sides bounded by a wall of said tip, a portion of said rib extends from said first sidewall and terminates prior to said second sidewall, and said first and second cooling cavities have respective first and second outlets into said plenum, said first and second outlets both defined along said floor such that said first and second outlets are spaced apart by said rib.

2. The component as recited in claim 1 , wherein said component is a blade.

3. The component as recited in claim 1 , wherein said component is a vane.

4. The component as recited in claim 1 , wherein said rib extends across said plenum.

5. The component as recited in claim 1 , wherein said rib defines a surface that constricts a flow of cooling fluid that exits at least one of said first cooling cavity and said second cooling cavity into said plenum.

6. The component as recited in claim 5 , wherein said first and second cooling cavities extend radially inward from said rib towards said base.

7. The component as recited in claim 1 , comprising a third cooling cavity that merges into said plenum.

8. The component as recited in claim 7 , wherein said third cooling cavity exits adjacent to another rib.

9. The component as recited in claim 1 , wherein said rib includes a radially extending face that is offset from at least one of said first and second outlets.

10. The component as recited in claim 1 , wherein said rib includes a radially extending face that is offset from said first outlet and said second outlet, and said radially extending face opposes one of said first and second sidewalls.

11. The component as recited in claim 10 , wherein said radially extending face slopes away from said floor.

12. A gas turbine engine, comprising:

a component disposed in at least one of a compressor section and a turbine section, wherein said component includes a body that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending radially from a base to a tip, said component having an internal cooling scheme comprising:

a cooling cavity that merges into a plenum;

a rib that extends from said first sidewall into said plenum to control expansion of a cooling fluid from said cooling cavity into said plenum, wherein said rib extends radially between opposing sides of said plenum such that said cooling cavity extends along said first sidewall, one of said opposing sides defining a floor and another one of said opposing sides bounded by a wall of said tip, said rib extends transversely between said opposing sides, a portion of said rib extends from said first sidewall and terminates prior to said second sidewall, and said cooling cavity has an outlet into said plenum, said outlet defined along said floor.

13. The gas turbine engine as recited in claim 12 , wherein said cooling cavity includes a first cooling cavity and a second cooling cavity each merging into said plenum, said first and second cooling cavities separated by said rib, and wherein said outlet includes and outlet of said first cooling cavity and an outlet of said second cooling cavity.

14. The gas turbine engine as recited in claim 13 , wherein said outlet of said first cooling cavity and said outlet of said second cooling cavity are spaced apart from said rib.

15. A core assembly for fabricating a component, comprising:

a first core that defines a first cooling cavity of a component;

a second core that defines a second cooling cavity of said component;

a partial rib that extends from said first core and said second core and defines a plenum of said component; and

at least one cut-out in said partial rib that defines a rib in said component, wherein said partial rib extends radially between opposing sides of said plenum such that said first cooling cavity and said second cooling cavity extend along a first sidewall of said component on opposed sides of said partial rib, said partial rib extends transversely between said opposing sides, a portion of said partial rib extends from said first sidewall of said component and terminates prior to a second sidewall of said component, said first core and said second core arranged such that said first and second cooling cavities have respective first and second outlets into said plenum, and said first and second outlets both defined along a common one of said opposing sides such that said first and second outlets are spaced apart by said partial rib.

16. The core assembly as recited in claim 15 , wherein said component is a completed component.

17. The core assembly as recited in claim 15 , comprising a third core that defines a third cooling cavity of said component.

18. The core assembly as recited in claim 17 , wherein said partial rib extends from said third core.

19. The core assembly as recited in claim 15 , wherein said at least one cut-out includes a plurality of cut-outs disposed on opposing faces of said partial rib.