| 摘要 |
A method for determining performance levels of at least one turbine engine propeller in an incident air flow (V) including an axial component (Vz) and a tangential component (Vθ), the propeller being modelled by a defined generalized theoretical model (Mg), for plural blade angles (β) of the propeller, by a set of adimensional coefficients, including at least one generalized advance coefficient (Jg), a generalized power coefficient (CPg), and a generalized traction coefficient (CTg) defined by formulae: { J g = v z u - vθ C Tg (β) = T (β)ρ· ( u - vθ) 2 · D 2 C Pg (β) = P (β)ρ· ( u - vθ) 3 · D 2 wherein the generalized theoretical model (Mg) of the propeller is parameterized with input conditions of the turbine engine, including at least the axial component (Vz), the tangential component of the incident air flow (Vθ), the blade angle (β) and the drive speed (u) of the propeller; and at least the traction performance level (T) and power performance level (P) of the propeller are derived from the parameterized generalized theoretical model (Mg). |
