Propeller for turboshaft engine e.g. turbojet, of aircraft, has blade feet projected radially from inner side of nacelle that is located near another nacelle of turboshaft engine, and compression units compressing air flow

摘要

The propeller (32, 36) has a careenage forming a nacelle (N1) and multiple blades (48, 55), where each blade comprises aerodynamic parts (60, 61) projecting radially from outside the nacelle. Blade feet (58, 62) are projected radially from an inner side of the nacelle. The nacelle is levelled with an upstream part (M2) and/or a downstream part (V1) and located near another nacelle (N2) of a turboshaft engine (1). Compression units (C1, C2) compress air flow. The compression units comprise a compression blade ring distributed on the former nacelle.