Hub of an intermediate casing for an aircraft turbojet engine comprising doors with contoured geometry
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United States of America Patent
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Apr 17, 2018
Issued Date -
N/A
app pub date -
Jul 23, 2014
filing date -
Jul 23, 2013
priority date (Note) -
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Abstract
A hub of an intermediate casing for an aircraft turbojet engine, including an inner shell intended to define a primary flow space of a primary gas stream into a turbojet engine, and at least one intermediate space, the inner shell being provided with at least one primary port and at least one movable door forming a primary air passage conduit, the 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. The primary conduit has an inner surface including, from upstream to downstream, a converging upstream part, then a nonconverging downstream part, in which the downstream part includes two portions of downstream side surface, and in which the upstream portion further includes two portions of upstream side surface.
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