Method and apparatus for operating gas turbine engine heat exchangers

1. A method for assembling a turbine engine to facilitate reducing an operating temperature of a fluid utilized therein, the turbine engine including a core gas turbine engine, a splitter circumscribing the core gas turbine engine, the fan assembly disposed upstream from the core gas turbine engine, a fan casing substantially circumscribing the fan assembly, and a bypass duct that is defined between the fan casing and the splitter, said method comprising: providing an arcuate liquid-to-air heat exchanger that includes: a plurality of channels extending therethrough; a plurality of cooling fins coupled to each of the plurality of channels and configured to receive a flow of air to facilitate reducing a temperature of a liquid flowing through the channels; at least one attachment portion formed unitarily with the heat exchanger, the heat exchanger having a first width, the at least one attachment portion having a second width that is less than the first width such that a recess is defined radially inward from the at least one attachment portion; and at least one inner plate coupled at the recess to facilitate directing airflow over the cooling fins; bending the heat exchanger such that the heat exchanger has a circumferential and axial profile that is substantially conforms to the circumferential and axial profile of the fan duct at the location within the fan duct where the air cooled heat exchanger is mounted; and coupling the heat exchanger within in the bypass duct.

2. A method in accordance with claim 1 further comprising coupling the heat exchanger to an interior surface of the fan casing such that the heat exchanger is positioned upstream or downstream from the fan assembly.

3. A method in accordance with claim 1 wherein assembling a heat exchanger assembly further comprises:

forming a heat exchanger having a plurality of openings extending therethrough;

coupling a plurality of cooling fins to the heat exchanger; and

coupling at least one cover plate to the heat exchanger such that airflow channeled through the bypass duct is channeled over the cooling fins to facilitate reducing the operating temperature of a fluid channeled through the openings.

4. A method in accordance with claim 3 wherein forming a heat exchanger further comprises forming a heat exchanger having a substantially square cross-sectional profile unitarily with the cooling fins.

5. A method in accordance with claim 3 wherein coupling a plurality of cooling fins to the heat exchanger such that the cooling fins are substantially perpendicular to the openings.

6. A method in accordance with claim 1 further comprising:

coupling the radially outer plate to the radially inner plate such that a cavity is defined between the heat exchanger and the outer plate;

coupling a plurality of standoffs between the outer plate and the heat exchanger to facilitate securing the heat exchanger in a relatively fixed position; and

positioning an insulating material between adjacent standoffs, the outer plate, and the heat exchanger.

7. A gas turbine engine assembly comprising:

a core gas turbine engine;

a nacelle circumscribing said core gas turbine engine; and

a heat exchanger assembly disposed within said nacelle, said heat exchanger assembly comprising:

an arcuate liquid-to-air heat exchanger that is circumferentially oriented and is configured to be contacted by a flow of air within the nacelle and outside of the core gas turbine engine said heat exchanger comprising:

a plurality of channels extending therethrough;

a plurality of cooling fins coupled-thereto such that air can flow over said cooling fins to facilitate reducing a temperature of a liquid flowing through said channels;

at least one attachment portion formed unitarily with said heat exchanger, said heat exchanger having a first width, said at least one attachment portion having a second width that is less than the first width such that a recess is defined radially inward from said at least one attachment portion; and

at least one inner plate coupled at the recess to facilitate directing airflow over said cooling fins.

8. A gas turbine engine assembly in accordance with claim 7 wherein said heat exchanger assembly has a profile that is substantially similar to a profile of said nacelle.

9. A gas turbine engine assembly in accordance with claim 7 wherein said heat exchanger is formed unitarily with said cooling fins.

10. A gas turbine engine assembly in accordance with claim 7 wherein said heat exchanger has a substantially rectangular cross-sectional profile and wherein each of said channels has a substantially rectangular cross-sectional profile.

11. A gas turbine engine assembly in accordance with claim 7 further comprising:

an outer plate coupled to said at least one inner plate such that a cavity is defined between said heat exchanger and said outer plate;

a plurality of standoffs coupled between said outer plate and said heat exchanger to facilitate securing said heat exchanger in a substantially fixed position; and

an insulating material positioned between adjacent standoffs, said outer plate, and said heat exchanger.

12. A gas turbine engine assembly in accordance with claim 7 wherein said cooling fins are oriented substantially perpendicular to said channels.

13. A gas turbine engine assembly in accordance with claim 7 wherein said heat exchanger assembly is coupled to said nacelle.