ISOTHERMALIZED COOLING OF GAS TURBINE ENGINE COMPONENTS

1 . A component, comprising:

a first wall section;

a second wall section spaced from said first wall section;

a plurality of branches between said first wall section and said second wall section; and

a heat transfer device disposed either between adjacent branches of said plurality of branches or inside at least one branch of said plurality of branches.

2 . The component as recited in claim 1 , wherein said heat transfer device includes a wick structure and a working medium.

3 . The component as recited in claim 2 , wherein said wick structure includes a sintered metal powder.

4 . The component as recited in claim 1 , wherein said heat transfer device is an enclosed structure that holds a working medium.

5 . The component as recited in claim 1 , comprising passages that extend between said adjacent branches of said plurality of branches.

6 . The component as recited in claim 5 , wherein said heat transfer device is located within one of said passages.

7 . The component as recited in claim 1 , wherein said component is an additively manufactured component.

8 . The component as recited in claim 1 , wherein said heat transfer device is disposed between said adjacent branches of said plurality of branches and a second heat transfer device is disposed inside said at least one branch of said plurality of branches.

9 . The component as recited in claim 1 , wherein said heat transfer device includes an evaporation section and a condenser section.

10 . The component as recited in claim 9 , wherein a working medium of said heat transfer device moves between said evaporation section and said condenser section in response to absorbing or releasing heat.

11 . The component as recited in claim 9 , wherein locations of said evaporation section and said condenser section vary based on localized temperatures of the component.

12 . The component as recited in claim 1 , wherein said first wall section and said second wall section are part of a blade, a vane, a blade outer air seal (BOAS), a combustor panel, or a turbine exhaust case liner of a gas turbine engine.

13 . The component as recited in claim 1 , wherein said heat transfer device includes a first working medium and a second heat transfer device of the component includes a second working medium.

14 . A component, comprising:

a wall;

a lattice structure arranged inside the wall; and

said lattice structure including a plurality of nodes, a plurality of branches that extend between said plurality of nodes, a plurality of passages extending between said plurality of nodes and said plurality of branches, and a heat transfer device adapted to transfer thermal energy within said lattice structure by selectively evaporating and condensing a working medium.

15 . The component as recited in claim 14 , wherein said lattice structure is a vascular engineered lattice structure.

16 . The component as recited as recited in claim 15 , wherein said vascular engineered lattice structure is configured such that airflow is communicated through said plurality of passages and said heat transfer device is disposed inside at least one node of said plurality of nodes or inside at least one branch of said plurality of branches.

17 . The component as recited in claim 15 , wherein said vascular engineered lattice structure includes a hollow lattice structure in which airflow is communicated inside said plurality of nodes and said plurality of passages and said heat transfer device is disposed within at least one passage of said plurality of passages.

18 . The component as recited in claim 14 , wherein said working medium is at least partially carried by a wick structure of said heat transfer device.

19 . The component as recited in claim 18 , wherein said wick structure includes a sintered metal powder.

20 . The component as recited in claim 14 , wherein said heat transfer device is an enclosed structure that holds said working medium.