IMPROVING THE DYNAMIC BEHAVIOR OF THE DRIVE SHAFT OF THE FAN ROTOR OF AN AERONAUTICAL PROPULSION SYSTEM

An aeronautical propulsion system (1) has a mean internal radius Rm_a of the high-pressure turbine (7) satisfying formula (I), where: FN is the thrust of the propulsion system (1); BPR is the dilution rate of the propulsion system (1); and I = 0.16 millimeters by Newton (mm/N) and J = 28 millimeters...

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Bibliographische Detailangaben
1. Verfasser:	ESCURE, Didier
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	An aeronautical propulsion system (1) has a mean internal radius Rm_a of the high-pressure turbine (7) satisfying formula (I), where: FN is the thrust of the propulsion system (1); BPR is the dilution rate of the propulsion system (1); and I = 0.16 millimeters by Newton (mm/N) and J = 28 millimeters. Un système propulsif (1) aéronautique présente un rayon moyen d'un alésage Rm_a de la turbine haute pression (7) respecte la formule (I) où : FN est la poussée du système propulsif (1); BPR est le taux de dilution du système propulsif (1); et I = 0,16 millimètres par Newton (mm/N) et J = 28 millimètres.