US 11,952,950 B2
Axial turbine engine, and rectifier stage with variable orientation vanes for an axial turbine engine
Lilian Yann Dumas, Bois le Roi (FR); Baptiste René Roger Batonnet, Sezanne (FR); and Romain Nicolas Lagarde, La Queue en Brie (FR)
Assigned to SAFRAN AIRCRAFT ENGINES SAS, Paris (FR)
Appl. No. 17/628,608
Filed by SAFRAN AIRCRAFT ENGINES SAS, Paris (FR)
PCT Filed Jul. 23, 2020, PCT No. PCT/EP2020/070856
§ 371(c)(1), (2) Date Jan. 20, 2022,
PCT Pub. No. WO2021/013957, PCT Pub. Date Jan. 28, 2021.
Claims priority of application No. 1908399 (FR), filed on Jul. 24, 2019.
Prior Publication US 2022/0275762 A1, Sep. 1, 2022
Int. Cl. F02C 9/20 (2006.01); F01D 17/16 (2006.01); F02C 6/08 (2006.01); F02C 9/18 (2006.01); F04D 27/02 (2006.01); F04D 29/56 (2006.01)
CPC F02C 9/20 (2013.01) [F01D 17/162 (2013.01); F02C 6/08 (2013.01); F02C 9/18 (2013.01); F04D 27/023 (2013.01); F04D 29/563 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A turbomachine, said turbomachine comprising:
a compression device with a rectifier stage with variable orientation vanes;
a combustion chamber downstream of the compression device;
a turbine device downstream of the combustion chamber; and
a leak passage of air compressed by the compression device, between the compression device and the turbine device, in order to cool the turbine device;
wherein the rectifier stage is configured to modulate a section of the leak passage according to an orientation of the vanes of the rectifier stage; and
wherein the rectifier stage comprises an inner ring comprising an upstream edge facing a downstream edge of an annular duct on an intermediate casing of the turbomachine, with a clearance between the edges forming a leak passage with a non-modulating section in parallel with the leak passage with a modulating section formed by the rectifier stage.