Patent ID: 11927133
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  G  D | IPC B  D  F  G

Claim 10:
11. The aerodynamic structuring assembly according to claim 9, wherein said wall is located at the position of one of the following areas of the aircraft turbine engine:
a tip (280) of a central air intake cone (28),
a leading edge (120) of a fan wheel (12),
an air intake lip (300) of a fairing (30) surrounding an annular secondary air stream (14,B) successively surrounding, along an axis (X) of revolution of the turbine engine around which the fan wheel (12) rotates, an annular primary air stream (16,A) flowing into a low-pressure compressor (18), a high-pressure compressor (20), an annular combustion chamber (22), a high-pressure turbine (24) and a low-pressure turbine (26),
leading edges (310) of stator blades (31),
leading edges (330) of radial arms (33),
a leading edge (270) beginning axially upstream from the low-pressure compressor (18) and allowing a separation of air between the annular primary air stream (16, A) and annular secondary air stream (14,B), at the annular primary air stream (16, A).