Optimization of the high-pressure body of a high-bypass engine

Abstract

An aeronautical propulsion system (1) comprising high-pressure bearings (12a, 12b) including a forward bearing (12a) extending upstream of a combustion chamber of the propulsion system (1) and a rear bearing (12b) extending downstream of the combustion chamber, wherein a bypass ratio of the propulsion system (1) is greater than or equal to 8, a fan cross-section pressure ratio is less than or equal to 1.45, and the high-pressure compressor (5) is dimensioned to satisfy the following formula: where: XN is the limiting speed of the high-pressure shaft (10) (in rpm); Ri is an average internal radius of the high-pressure compressor (5) (in m); and L is an axial distance between a center of gravity (G12a) of the forward bearing (12a) and a center of gravity (G12b) of the rear bearing (12b) (in m). Figure for the abstract: Fig. 1

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