Integrated thermal management with nacelle laminar flow control for geared architecture gas turbine engine

1. A thermal management system for a gas turbine engine comprising:

a geared architecture to drive a fan at a lower speed than a low spool;

a heating compartment located within an inlet of a fan nacelle, the fan nacelle surrounds the fan; and

a heat exchanger in fluid communication with said geared architecture and said heating compartment.

2. The system as recited in claim 1 , wherein said heat exchanger is in fluid communication with said geared architecture and said heating compartment via a heat exchange fluid.

3. The system as recited in claim 1 , wherein said heat exchanger is in fluid communication with said geared architecture through a fluid plenum.

4. The system as recited in claim 3 , wherein said fluid plenum at least partially surrounds said geared architecture.

5. The system as recited in claim 1 , wherein the heat exchanger is in fluid communication with an oil system of said geared architecture.

6. The system as recited in claim 1 , wherein said fan and said low spool are defined along an engine axis.

7. The system as recited in claim 6 , further comprising a high spool along the engine axis.

8. A gas turbine engine comprising:

a geared architecture to drive a fan at a lower speed than a low spool, wherein said fan and said low spool are defined along an engine axis;

a heating compartment within an inlet of a nacelle, said fan located within said nacelle; and

a heat exchanger in fluid communication with said heating compartment, the heat exchanger located within the nacelle generating a thermal gradient that encourages a sustained stabilization of a boundary-layer adjacent to the nacelle;

a fluid plenum that at least partially surrounds the geared architecture, said heat exchanger in fluid communication with said geared architecture.

9. The gas turbine engine as recited in claim 8 , wherein said nacelle is a fan nacelle.

10. A method of thermal management for a gas turbine engine, comprising:

vaporizing a heat exchange fluid to form a vaporized heat exchange fluid with heat from a geared architecture that drives a fan at a lower speed than a low spool, wherein said fan and said low spool are defined along an engine axis; and

communicating the vaporized heat exchange fluid to a heating compartment located within an inlet of a nacelle.

11. The method as recited in claim 10 , further comprising deicing the inlet of the nacelle with the vaporized heat exchange fluid.

12. The method as recited in claim 10 , further comprising generating a thermal gradient that encourages a sustained stabilization of a boundary-layer over the nacelle to facilitate laminar airflow.

13. The method as recited in claim 10 , further comprising generating a thermal gradient that encourages a sustained stabilization of a boundary-layer over the inlet of the nacelle to facilitate laminar airflow.

14. The method as recited in claim 10 , further comprising communicating the heat exchange fluid into a fluid plenum that at least partially surrounds the geared architecture.

15. The method as recited in claim 10 , wherein vaporizing the heat exchange fluid is performed by heat from the geared architecture.

16. The method as recited in claim 10 , further comprising communicating the vaporized heat exchange fluid from the heat exchanger as a vapor.

17. The method as recited in claim 10 , further comprising communicating the vaporized heat exchange fluid to the heating compartment as a vapor.