TURBINE ENGINE FOR AN AIRCRAFT WITH HEAT EXCHANGER

The invention relates to a turbine engine comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downstream of a rotor and in a diffusion channel in order to slow an...

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Bibliographische Detailangaben
1. Verfasser:	PRINCIVALLE, Rémy, Henri, Pierre
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS 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 comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downstream of a rotor and in a diffusion channel in order to slow an air flow upstream of a heat exchanger.