ASSEMBLY MADE UP OF AT LEAST ONE AIRCRAFT TURBINE ENGINE AND AN INERTIAL MEASUREMENT UNIT, AND ASSOCIATED METHOD

The invention relates to an assembly comprising at least one turbine engine (2) for an aircraft, comprising a casing in which at least one rotary body is mounted to allow propulsion of the aircraft, with an air flow flowing from upstream to downstream in the turbine engine (2), at least one inertial...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	BESSAH, Naïm, LEYNAUD, Robin, PELAGATTI, Euridice, CUNY, Marion, GENTILS, Romuald Muriel
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROL OR REGULATING SYSTEMS IN GENERAL CONTROLLING CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS FUNCTIONAL ELEMENTS OF SUCH SYSTEMS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS PHYSICS REGULATING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to an assembly comprising at least one turbine engine (2) for an aircraft, comprising a casing in which at least one rotary body is mounted to allow propulsion of the aircraft, with an air flow flowing from upstream to downstream in the turbine engine (2), at least one inertial measurement unit (3) mounted in the turbine engine (2), the inertial measurement unit (3) being configured to measure at least one turbine engine load applied to the turbine engine during a flight of the aircraft, and at least one computer configured to determine at least one malfunction of the turbine engine (2) on the basis of the turbine engine load. Un ensemble comprenant au moins une turbomachine (2) pour un aéronef comprenant un carter dans lequel est monté au moins un corps rotatif pour permettre la propulsion de l' aéronef, un flux d' air circulant d' amont vers l' aval dans la turbomachine (2), au moins une centrale inertielle (3) montée dans la turbomachine (2), la centrale inertielle (3) étant configurée pour mesurer au moins une charge turbomachine appliquée à la turbomachine au cours d' un vol de l' aéronef et au moins un calculateur configuré pour déterminer au moins un dysfonctionnement de la turbomachine (2) à partir de la charge turbomachine.