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.
GAS TURBINE ENGINE WITH LOWER BIFURCATION HEAT EXCHANGER
GASTURBINENMOTOR MIT EINEM WÄRMETAUSCHER IN EINER UNTEREN GABELUNG
MOTEUR DE TURBINE À GAZ COMPORTANT UN ÉCHANGEUR DE CHALEUR DANS UNE BIFURCATION INFÉRIEURE
2018-09-05
Patent
Electronic Resource
English
Gas turbine engine with thermoelectric cooling air heat exchanger
European Patent Office | 2020
|