Turboprop unit for aircraft with improved aerodynamic installation

Abstract

A turboprop engine includes a power jet mounted coaxially to the engine axis (X-X′), and has a fan case and a gas ejecting system provided with two afterbody half-cowlings (10b) each of which is pivotable around an axis (A2) between open and closed positions, wherein the half-cowlings are connected to the downstream of the fan case through a ‘V-blade/V-groove’ system. In a first embodiment, the pivot axes (A2) make an angle α>3° to the engine axis (X, X′) and a joint plane (Z2-Z2) between the afterbody half-cowlings and the downstream of the fan case makes to the plane (Y, Y′) perpendicular to the engine axis (X, X′) an angle β in such a way that the difference between the angle α and the angle β is less than or equal to 3°. In the other embodiment, the axes are converged to each other in a downstream direction.

Dependencies are inferred from the claim text.