TURBINE ENGINE FOR AIRCRAFT WITH HEAT EXCHANGER

The invention relates to a turbine engine (1) comprising an unshrouded propeller (14) propelling a tertiary flow (13), a fan (12), a compressor (4) compressing a primary flow (F1), and an annular passage (19) for the flow of a secondary flow (F2) downstream of the fan (12); the annular passage (19)...

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Bibliographische Detailangaben
1. Verfasser:	PRINCIVALLE, Rémy, Henri, Pierre
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a turbine engine (1) comprising an unshrouded propeller (14) propelling a tertiary flow (13), a fan (12), a compressor (4) compressing a primary flow (F1), and an annular passage (19) for the flow of a secondary flow (F2) downstream of the fan (12); the annular passage (19) accommodating an annular row of rectifier blades (22) and at least one heat exchanger (24) downstream of the row of blades (22); a plurality of diffusion passages being provided upstream of the at least one exchanger (24), each passage being delimited circumferentially by a pressure side and by a suction side of two circumferentially adjacent blades (22) and by at least one fin supported by at least one of the two circumferentially adjacent blades (22).