Electrical strut for a turbine engine

1. An airfoil for a turbine engine, the airfoil comprising:

an outer wall having a pressure side, a suction side, a leading edge, and a trailing edge, the outer wall defining an interior and separating the interior from an exterior, wherein the outer wall extends between the pressure side and the suction side to define a lateral direction, between the leading edge and the trailing edge to define a chord-wise direction, and between a root and a tip to define a span-wise direction; and

multiple electrical conduits extending from the exterior into the interior along the span-wise direction, at least one electrical conduit of the multiple electrical conduits comprising:

at least one conductor forming a cooling conduit with a hollow interior having a central axis along which at least a portion of a cooling flow path extends;

wherein the at least one conductor surrounds the cooling flow path; and

wherein the multiple electrical conduits are spaced from each other a first distance in the exterior and a second distance less than the first distance within the interior.

2. The airfoil of claim 1 , wherein the at least one conductor is an electric busbar.

3. The airfoil of claim 1 , wherein the at least one electrical conduit comprises multiple layers, the at least one conductor defining a first layer and an insulator defining a second layer surrounding the first layer and the insulator defining an exterior of the at least one electrical conduit.

4. The airfoil of claim 3 , comprising an electromagnetic shielding layer surrounding the exterior of the at least one electrical conduit.

5. The airfoil of claim 1 , wherein a cross-sectional area of each of the electrical conduits has a width oriented along the chord-wise direction and a height oriented along the lateral direction, the width and height together defining an aspect ratio of the cross-sectional area.

6. The airfoil of claim 5 , wherein the aspect ratio is between 1:4 and 4:1, inclusive of endpoints.

7. The airfoil of claim 5 , wherein the width is greater than the height.

8. The airfoil of claim 5 , wherein the width is less than the height.

9. The airfoil of claim 1 , wherein the multiple electrical conduits define a conduit grouping adapted for carrying three phase power.

10. The airfoil of claim 9 , wherein the conduit grouping further comprises a neutral line.

11. The airfoil of claim 1 , further comprising an interior wall defining a cooling passage within the airfoil and nested within the outer wall and wherein each of the electrical conduits is located within the cooling passage.

12. The airfoil of claim 1 wherein the cooling conduit is formed in a rounded rectangular shape.

13. A method of forming the airfoil of claim 1 , the method comprising:

forming the outer wall; and

extending each of the electrical conduits within the interior along the span-wise direction;

wherein a cross-sectional area of the at least one electrical conduit has a width oriented along the chord-wise direction and a height oriented along the lateral direction, the width and the height together defining an aspect ratio of the cross-sectional area; and

wherein the largest dimension measured along the lateral direction between the pressure side and the suction side defines a maximum thickness.

14. The method of claim 13 , further comprising orienting each of the electrical conduits within the interior to minimize the maximum thickness of the airfoil by minimizing the height.

15. The method of claim 13 , further comprising orienting each of the electrical conduits within the interior to maximize a stiffness of each of the electrical conduits by maximizing the height.

16. A turbine engine comprising:

an engine core;

a core casing surrounding the engine core;

at least one cowl surrounding the core casing;

a power converter located between the at least one cowl and the core casing;

an electrical generator disposed within the engine core;

at least one electrical strut having an outer wall defining an interior, separating the interior from an exterior, and extending radially between the engine core and the core casing; and

multiple electrical conduits extending from the exterior into the interior and electrically coupling the electrical generator to the power converter, at least one electrical conduit of the multiple electrical conduits comprising at least one conductor forming a cooling conduit with a hollow interior having a central axis along which at least a portion of a cooling flow path extends;

wherein the at least one conductor surrounds the cooling flow path; and

wherein the multiple electrical conduits are spaced from each other a first distance in the exterior and a second distance less than the first distance within the interior.

17. The turbine engine of claim 16 , wherein the electrical generator is located proximate an aft portion of the engine and the power converter is located proximate a forward portion of the engine.

18. The turbine engine of claim 16 , wherein the at least one electrical conduit comprises an electric busbar.

19. The turbine engine of claim 16 , wherein the outer wall defines an airfoil shape extending between a pressure side and a suction side to define a lateral direction, between a leading edge and a trailing edge to define a chord-wise direction, and between a root and a tip to define a span-wise direction, and wherein a cross-sectional area of the at least one electrical conduit has a width oriented along the chord-wise direction and a height oriented along the lateral direction, the width and height together defining an aspect ratio of the cross-sectional area.

20. The turbine engine of claim 19 , wherein a largest dimension measured along the lateral direction between the pressure side and suction side defines a maximum thickness of the airfoil and the multiple electrical conduits are oriented within the interior to minimize the maximum thickness of the airfoil by minimizing the height.