Heat exchanger supply plenum

1. A cooling system for a gas turbine engine, comprising:

an outer engine case structure;

an inner engine case structure disposed radially inward of the outer engine case structure, the inner engine case structure and the outer engine case structure defining a bypass duct;

a heat exchanger disposed between the outer engine case structure and the inner engine case structure;

a supply conduit disposed radially outward of the outer engine case structure, the supply conduit extending circumferentially about the outer engine case structure, the supply conduit fluidly coupled to the heat exchanger;

a return conduit disposed radially outward of the outer engine case structure and axially adjacent to the supply conduit, the return conduit extending circumferentially about the outer engine case structure, the return conduit fluidly coupled to the heat exchanger;

an insultation configured to enclose the supply conduit and the return conduit, the insulation defining a plenum, the supply conduit and the return conduit disposed within the plenum;

a first plurality of heat fins coupled to the supply conduit and extending from a first radially inner surface of the supply conduit, each heat fin in the first plurality of heat fins extending away from the outer engine case structure; and

a second plurality of heat fins coupled to the return conduit and extending from a second radially inner surface of the return conduit, each heat fin in the second plurality of heat fins extending away from the outer engine case structure.

2. The cooling system of claim 1 , wherein the supply conduit comprises a first annular tube, and wherein the return conduit comprises a second annular tube.

3. The cooling system of claim 1 , wherein the supply conduit and the return conduit are integral to the outer engine case structure.

4. The cooling system of claim 1 , wherein the outer engine case structure, the supply conduit, and the return conduit are a monolithic component.

5. The cooling system of claim 1 , wherein the supply conduit and the return conduit are radially adjacent to the outer engine case structure.

6. A cooling system for use in a gas turbine engine, comprising:

an outer engine case structure;

an inner engine case structure disposed radially inward of the outer engine case structure, the inner engine case structure and the outer engine case structure defining a bypass duct;

a heat exchanger disposed between the outer engine case structure and the inner engine case structure;

a supply conduit extending circumferentially about the outer engine case structure, the supply conduit fluidly coupled to the heat exchanger;

a return conduit extending circumferentially about the outer engine case structure, the return conduit fluidly coupled to the heat exchanger;

an axial wall disposed between and partially defining the supply conduit and the return conduit, the axial wall at least partially defining a first flow path within the supply conduit and a second flow path within the return conduit;

a first plurality of heat fins coupled to the supply conduit and extending from a first inner surface of the supply conduit, each heat fin in the first plurality of heat fins extending away from the outer engine case structure; and

a second plurality of heat fins coupled to the return conduit and extending from a second inner surface of the return conduit, each heat fin in the second plurality of heat fins extending away from the outer engine case structure.

7. The cooling system of claim 6 , wherein the axial wall comprises a cavity disposed between a first axial surface in the supply conduit and a second axial surface in the return conduit.

8. The cooling system of claim 6 , wherein the supply conduit, the return conduit, and the axial wall are integral to the outer engine case structure.

9. The cooling system of claim 6 , wherein the supply conduit and the return conduit each have a substantially rectangular cross-sectional shape.

10. The cooling system of claim 6 , further comprising insulation configured to enclose the supply conduit, the return conduit, and the axial wall.

11. The cooling system of claim 6 , wherein the supply conduit and the return conduit are annular in shape.

12. A gas turbine engine, comprising:

an outer engine case structure;

an inner engine case structure disposed radially inward of the outer engine case structure, the inner engine case structure and the outer engine case structure defining a bypass duct;

a heat exchanger disposed between the outer engine case structure and the inner engine case structure;

a supply conduit extending circumferentially about the outer engine case structure, the supply conduit fluidly coupled to the heat exchanger;

a return conduit disposed axially adjacent to the supply conduit, the return conduit extending circumferentially about the outer engine case structure, the return conduit fluidly coupled to the heat exchanger;

an insultation configured to enclose the supply conduit and the return conduit, the insulation defining a plenum, the supply conduit and the return conduit disposed within the plenum;

a first plurality of heat fins coupled to the supply conduit and extending from a first inner surface of the supply conduit, each heat fin in the first plurality of heat fins extending away from the outer engine case structure; and

a second plurality of heat fins coupled to the return conduit and extending from a second inner surface of the return conduit, each heat fin in the second plurality of heat fins extending away from the outer engine case structure.

13. The gas turbine engine of claim 12 , further comprising an axial wall disposed between the supply conduit and the return conduit.

14. The gas turbine engine of claim 13 , wherein the axial wall comprises a cavity disposed between a first axial surface in the supply conduit and a second axial surface in the return conduit.

15. The gas turbine engine of claim 12 , wherein the supply conduit, the return conduit, and the outer engine case structure are a monolithic component.