US 12,078,072 B2
Turbomachine module provided with a propeller and offset stator vanes
Paul Ghislain Albert Levisse, Moissy-Cramayel (FR); and Olivier Belmonte, Moissy-Cramayel (FR)
Assigned to Safran Aircraft Engines, Paris (FR)
Appl. No. 18/246,554
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Sep. 29, 2021, PCT No. PCT/FR2021/051682
§ 371(c)(1), (2) Date Mar. 24, 2023,
PCT Pub. No. WO2022/069835, PCT Pub. Date Apr. 7, 2022.
Claims priority of application No. 2009933 (FR), filed on Sep. 29, 2020.
Prior Publication US 2023/0366325 A1, Nov. 16, 2023
Int. Cl. F01D 17/16 (2006.01); F01D 9/04 (2006.01); F01D 25/24 (2006.01)
CPC F01D 17/162 (2013.01) [F01D 9/042 (2013.01); F01D 25/246 (2013.01); F05D 2240/12 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbomachine module with a longitudinal axis, comprising:
an un-ducted propeller driven in rotation about the longitudinal axis by a power shaft which is connected to at least one compressor rotor, and at least one straightener comprising a plurality of stator vanes extending along a radial axis perpendicular to the longitudinal axis from a stationary casing, the at least one straightener being disposed downstream of the propeller,
wherein the stationary casing is an inter-compressor casing arranged downstream of a low-pressure compressor, along the longitudinal axis,
wherein the inter-compressor casing comprises an annulus centered on the longitudinal axis provided with sleeves configured to carry the plurality of stator vanes, and
wherein the inter-compressor casing and the annulus are monobloc.