Title:
UNDUCTED TURBINE ENGINE COMPRISING STATOR BLADES HAVING DIFFERENT CHORDS
Document Type and Number:
WIPO Patent Application WO/2023/110701
Kind Code:
A8
Abstract:
The invention relates to an aircraft comprising at least one unducted turbine engine for the propulsion of the aircraft, the turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with respect to the longitudinal axis, each stator blade being defined, in a plane (PT) transverse to the longitudinal axis, by an angular position (θ); and at least one aerodynamic obstruction (OA) positioned close to the turbine engine. The stator of the turbine engine comprises stator blades having a first chord, referred to as conventional blades (51), and at least one stator blade having a second chord larger than the first chord, referred to as the elongate blade (52), said at least one elongate blade (52) being positioned in an interference angular range (PAI) defined opposite the aerodynamic obstacle (OA), so as to increase the straightening of the airflow from the rotor in the interference angular range (PAI).
Inventors:
LEBEAULT EVA JULIE (FR)
SOULAT LAURENT (FR)
SOULAT LAURENT (FR)
Application Number:
PCT/EP2022/085288
Publication Date:
September 07, 2023
Filing Date:
December 12, 2022
Export Citation:
Assignee:
SAFRAN AIRCRAFT ENGINES (FR)
International Classes:
F02C6/20; F02C7/20; F02K3/02
Attorney, Agent or Firm:
ARGYMA (FR)
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