Gas turbine engine component with flow separating rib
A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.
1. A component for a gas turbine engine, comprising:
a wall that extends about a cooling cavity, wherein said cooling cavity is a dual-fed cavity that is fed from at least two different locations; and
a rib that separates said cooling cavity into a first portion and a second portion that is fluidly isolated from said first portion;
wherein the component is an airfoil;
wherein said first portion is fed with a first cooling fluid from a first coolant source, and said second portion is fed with a second, different cooling fluid from a second coolant source, the first and second coolant sources being separate and distinct from the component;
wherein said first and second coolant sources are different stages of a compressor section or a turbine section;
wherein said first portion is an outer diameter portion and said second portion is an inner diameter portion of said cooling cavity; and
wherein said outer diameter portion defines a first serpentine passage and said inner diameter portion defines a second serpentine passage, the first and second serpentine passages bounded by said rib.
2. The component as recited in claim 1 , wherein said wall circumscribes said cooling cavity.
3. The component as recited in claim 1 , wherein said rib is offset from a midspan of said airfoil.
4. The component as recited in claim 3 , wherein said rib is defined at a location between 10% and 90% span or between 30% and 70% span of said airfoil.
5. The component as recited in claim 1 , further comprising a plurality of cooling features defined along said wall.
6. The component as recited in claim 5 , wherein said plurality of cooling features include pedestals that extend between opposed surfaces of said cooling cavity.
7. The component as recited in claim 5 , wherein said plurality of cooling features include trip strips that protrude from surfaces of said cooling cavity.
8. The component as recited in claim 1 , wherein said rib is skewed in a radial direction towards one of an inner diameter and an outer diameter of said airfoil.
9. The component as recited in claim 1 , wherein said rib extends between leading and trailing edges of said airfoil.
10. The component as recited in claim 1 , wherein said rib connects between opposing sides of said wall.
11. The component as recited in claim 1 , wherein said rib extends in an axial direction inside of said cooling cavity.
12. The component as recited in claim 1 , comprising a plurality of openings through portions of said wall associated with both said first portion and said second portion, wherein said plurality of openings are film cooling holes.
13. A gas turbine engine, comprising:
a compressor section;
a turbine section; and
a component that defines a cooling circuit that cools said component with a cooling fluid, said cooling circuit is disposed inside an airfoil of said component, said cooling circuit including:
a cooling cavity disposed inside of said component; and
an axial rib that divides said cooling cavity into a first portion and a second portion that is separate from said first portion;
wherein said first portion is fed with a first cooling fluid from a first coolant source, and said second portion is fed with a second, different cooling fluid from a second coolant source, the first and second coolant sources being separate and distinct from the component;
wherein said first and second coolant sources are different stages of said compressor section or said turbine section;
wherein said first portion is an outer diameter portion and said second portion is an inner diameter portion of said cooling cavity; and
wherein said outer diameter portion defines a first serpentine passage and said inner diameter portion defines a second serpentine passage, the first and second serpentine passages bounded by said rib.
14. The gas turbine engine as recited in claim 13 , wherein said rib fluidly isolates said first portion from said second portion.
15. The gas turbine engine as recited in claim 13 , further comprising a mid-turbine frame that includes said airfoil.
16. A component for a gas turbine engine comprising:
a wall that extends about a cooling cavity, wherein said cooling cavity is a dual-fed cavity that is fed from at least two different locations; and
a rib that separates said cooling cavity into a first portion and a second portion that is fluidly isolated from said first portion;
wherein the component is an airfoil;
wherein said first portion is fed with a first cooling fluid from a first coolant source, and said second portion is fed with a second, different cooling fluid from a second coolant source, the first and second coolant sources being separate and distinct from the component;
wherein said first portion is an outer diameter portion and said second portion is an inner diameter portion of said cooling cavity;
wherein said outer diameter portion defines a first serpentine passage and said inner diameter portion defines a second serpentine passage, the first and second serpentine passages bounded by said rib; and
wherein said rib is spaced apart from leading and trailing edges of said airfoil.
17. The component as recited in claim 16 , wherein said rib extends in an axial direction inside of said cooling cavity.
18. The component as recited in claim 16 , wherein said wall circumscribes said cooling cavity.
19. The component as recited in claim 16 , comprising a plurality of openings through portions of said wall associated with both said first portion and said second portion, wherein said plurality of openings are film cooling holes.
20. A component for a gas turbine engine comprising:
a wall that extends about a cooling cavity, wherein said cooling cavity is a duel-fed cavity that is fed from at least two different locations; and
a rib that separates said cooling cavity into a first portion and a second portion that is fluidly isolated from said first portion;
wherein the component is an airfoil;
wherein said first portion is fed with a first cooling fluid from a first coolant source, and said second portion is fed with a second, different cooling fluid from a second coolant source, the first and second coolant sources being separate and distinct from the component;
wherein said first and second coolant sources are different stages of a compressor section or a turbine section; and
wherein said first portion is circumferentially offset from said second portion.