Gas turbine engine with lower bifurcation heat exchanger
AssigneeUnited Technologies Corporation
InventorMatthew J. Forcier
Life of this patent
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Abstract
A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.
Claims20
A gas turbine engine comprising:
- a nacelle extending circumferentially around an engine core and defining a fan bypass duct that is substantially annular between an inner wall and an outer wall;
- a lower bifurcation structure extending between the inner wall and the outer wall and bifurcating the fan bypass duct, wherein the lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure;
- and
- a heat exchanger positioned in the bifurcation duct.
A gas turbine engine comprising:
- a nacelle extending circumferentially around an engine core and defining a fan bypass duct that is substantially annular between an inner wall and an outer wall;
- a lower bifurcation structure extending between the inner wall and the outer wall and bifurcating the fan bypass duct, wherein the lower bifurcation structure defines a bifurcation duct having a duct inlet positioned in the fan bypass duct at a front end of the lower bifurcation structure and has a duct outlet positioned in the fan bypass duct at a rear end of the lower bifurcation structure;
- and
- a heat exchanger positioned in the bifurcation duct.
A method comprising:
- flowing air along a first flow path through a fan bypass duct defined by a nacelle of a gas turbine engine;
- flowing air from the fan bypass duct through a heat exchanger positioned in a bifurcation duct extending through a lower bifurcation structure of the fan bypass duct along a second flow path;
- and
- opening the nacelle to expose a core of the gas turbine engine such that a first side surface of the fan bypass duct is separated from a second side surface of the fan bypass duct.
Dependencies are inferred from the claim text.