Patent ID: 7681833

Claim:
A turboprop unit for an aircraft, comprising: a jet engine having a fan casing and a gas exhaust system coaxial with an engine axis, the gas exhaust system including two afterbody half-cowlings, each hinged about a hinge axis to move from an open maintenance position to a closed position, the afterbody half-cowlings also connected, in the closed position, to a downstream end of the fan casing via a V-blade/V-groove structure for sealing and strain transmission, wherein the hinge axes forms an angle α with the engine axis, wherein the angle α is greater than 3°, and wherein a joint plane between the afterbody half-cowlings and the downstream end of the fan casing forms an angle β with a perpendicular plane perpendicular to the engine axis such that a difference between the angle α and the angle β is less than or equal to 3°.