US 12,281,599 B2
Stator part of a turbomachine comprising a blade and a fin defining between them a decreasing surface from upstream to downstream in the gas flow direction
Gabriel Jacques Victor Mondin, Moissy-Cramayel (FR); and William Henri Joseph Riera, Moissy-Cramayel (FR)
Assigned to SAFRAN, Paris (FR)
Appl. No. 18/684,371
Filed by SAFRAN, Paris (FR)
PCT Filed Aug. 11, 2022, PCT No. PCT/FR2022/051578
§ 371(c)(1), (2) Date Feb. 16, 2024,
PCT Pub. No. WO2023/021258, PCT Pub. Date Feb. 23, 2023.
Claims priority of application No. 2108792 (FR), filed on Aug. 20, 2021.
Prior Publication US 2024/0218802 A1, Jul. 4, 2024
Int. Cl. F01D 9/04 (2006.01); F01D 5/14 (2006.01)
CPC F01D 9/041 (2013.01) [F05D 2240/12 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A stator part of a turbomachine comprising:
a platform,
a blade, and
a fin,
the fin comprising an upstream end and a downstream end, with reference to a general gas flow direction through the turbomachine,
the blade and the fin extending from the platform,
the platform, an extrados of the blade and the fin defining therebetween a gas flow channel,
the channel having a section in a plane normal to an axis of the turbomachine, the section having a surface area, the surface area continuously and monotonously decreasing from the upstream end to the downstream end,
wherein the fin comprises a ridge in a plane normal to the axis of the turbomachine, the ridge being contiguous to the channel, the ridge presenting an inclination relative to the platform, the inclination decreasing from upstream to downstream.