Thermal management system integrated pylon
A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes.
1. A thermal management system for a gas turbine engine comprising:
a bifurcation area;
at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine, said at least one heat exchanger positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine;
wherein said at least one heat exchanger includes first and second heat exchangers, said first and second heat exchangers mounted within a common plenum defined by said bifurcation area to share a common inlet; and
wherein first and second exits are formed, in part, by a split in the plenum downstream of said inlet.
2. The system as recited in claim 1 , wherein said bifurcation area is at least partially within a pylon structure.
3. The system as recited in claim 1 , wherein said bifurcation area is forward of a pylon structure.
4. The system as recited in claim 1 , wherein said bifurcation area is at least partially within a bifurcation.
5. The system as recited in claim 1 , wherein said at least one heat exchanger is mounted at least partially within a pylon structure.
6. The system as recited in claim 1 , wherein said at least one heat exchanger is mounted at least partially within an upper bifurcation.
7. The system as recited in claim 1 , wherein said at least one heat exchanger is mounted forward of a pylon structure.
8. The system as recited in claim 3 , wherein said at least one heat exchanger is mounted at least partially within an upper bifurcation.
9. The system as recited in claim 1 , wherein at least one flow vane is positioned on one side of said split, downstream of one of said first and second heat exchangers, leading to one of said first and second exits.
10. The system as recited in claim 9 , wherein said at least one flow vane includes a plurality of flow vanes, including a modulated flow vane to modulate an exit airflow.
11. The system as recited in claim 1 , wherein said first and second heat exchangers are positioned on opposite sides of said split in said plenum.
12. The system as recited in claim 1 , wherein said first and second heat exchangers are separate heat exchangers, and are spaced apart from one another.
13. A thermal management system for a gas turbine engine comprising:
a bifurcation area;
at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine;
wherein said at least one heat exchanger comprises a first heat exchanger and a second heat exchanger, said at least one heat exchanger positioned entirely downstream of an outlet of a fan case and a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine.
14. The system as recited in claim 13 , wherein said first heat exchanger and said second heat exchanger are mounted within a common plenum defined by said bifurcation area to share a common inlet.
15. A thermal management system for a gas turbine engine comprising:
a bifurcation area;
at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine;
wherein said at least one heat exchanger comprises a first heat exchanger and a second heat exchanger;
wherein said first heat exchanger and said second heat exchanger are mounted within separate plenums on either side of a central inlet guide vane defined by said bifurcation area, said first heat exchanger and said second heat exchanger each being positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said gas turbine engine and a fan nacelle of said gas turbine engine; and
wherein said central inlet guide vane defines a first inlet for said first heat exchanger and a second inlet for said second heat exchanger.
16. The system as recited in claim 15 , wherein said first heat exchanger and said second heat exchanger communicate through a respective first and second exit.
17. The system as recited in claim 15 , wherein said central inlet guide vane is spaced downstream of a fan section of the gas turbine engine.
18. A thermal management system for a gas turbine engine comprising:
a bifurcation area;
at least one heat exchanger mounted within said bifurcation area in communication with a bypass flow from the gas turbine engine, said at least one heat exchanger positioned downstream of a fan strut, said fan strut spanning between a core nacelle of said as turbine engine and a fan nacelle of said gas turbine engine; and
wherein said at least one heat exchanger is positioned entirely downstream of a fan case of said gas turbine engine.