| 摘要 |
The invention concerns a hub (1) of an intermediate casing (2) for an aircraft turbojet engine, comprising an inner shell (4) intended to define a primary flow space (40) of a primary gas stream into a turbojet engine, and at least one intermediate space (5), the inner shell being provided with at least one primary port (44) and at least one movable door (100) forming a primary air passage conduit, said door being capable of collecting, from the primary port, air flowing in the primary gas space and of sending the air collected in this way, via the intermediate space, towards a secondary air passage conduit (200), said hub being characterised in that the primary conduit has an inner surface comprising, from upstream to downstream, a converging upstream part, then a non-converging downstream part, in which the downstream part comprises two portions of downstream side surface, and in which the upstream portion further comprises two portions of upstream side surface, each portion of upstream side surface defining, with a respective downstream side surface, a side part of the inner surface, each portion of downstream side surface having a length in an upstream-to-downstream direction representing between 30% and 50% of the curvilinear length of the corresponding side part, from upstream to downstream. |
