Patent ID: 9003770
Filing Date: 2015-04-14
Classification: B64D,F01D,F02K,F05D

Abstract:
1. A nacelle rear assembly for a turbojet engine comprising: a cowl being located radially outside of a pod-shaped internal structure, said pod-shaped internal structure comprising an upstream part and a downstream part which form together a fairing for a gas generator, wherein said downstream part of said pod-shaped internal structure is of an O-duct type and said downstream part is configured to slide in an axial direction between an operating position and a maintenance position situated downstream of said operating position, wherein in the operating position, the downstream part covers the gas generator of said turbojet engine and defines an annular cold air flow path with said cowl, wherein the downstream part of said pod-shaped internal structure is configured to be detached from said upstream part of said pod-shaped internal structure, and said upstream part comprises two doors configured to pivotably open outward, wherein an inside diameter of an upstream edge of said downstream part is greater than a largest diameter of said gas generator, so that said downstream part of said pod-shaped internal structure is configured to slide without blockage in relation to said gas generator, and