US 12,359,580 B2
Turbine engine for an aircraft
Victor Henri Marius Varenne, Moissy-Cramayel (FR); Arnaud Baudran, Moissy-Cramayel (FR); Antoine Jean-Philippe Beaujard, Moissy-Cramayel (FR); and David René Pierre Le Cair, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/839,141
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Feb. 20, 2023, PCT No. PCT/FR2023/050240
§ 371(c)(1), (2) Date Aug. 16, 2024,
PCT Pub. No. WO2023/161582, PCT Pub. Date Aug. 31, 2023.
Claims priority of application No. 2201543 (FR), filed on Feb. 22, 2022.
Prior Publication US 2025/0154876 A1, May 15, 2025
Int. Cl. F01D 9/06 (2006.01); F01D 25/12 (2006.01)
CPC F01D 9/065 (2013.01) [F01D 25/12 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2260/2212 (2013.01); F05D 2260/22141 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A turbomachine for aircraft, the turbomachine being intended to propel, towards a downstream side, a flow of air entering from an upstream side, said turbomachine having a primary annular flow path and a cold flow channel extending around the primary annular flow path, said turbomachine comprising:
an impeller arranged upstream of a first annular wall, the first annular wall separating the primary annular flow path from the cold flow channel,
in the primary annular flow path, from upstream to downstream, a compressor, a combustion chamber, a first turbine and a second turbine, the compressor having an input stage and an output stage, the first turbine having a first turbine rotor and the second turbine having a second turbine rotor,
a shaft assembly for rotating the compressor and the impeller about an axis of rotation, the shaft assembly comprising a first connecting shaft and a second connecting shaft, the first connecting shaft being rotatably connected to the second turbine rotor, the second connecting shaft being rotatably connected to the first turbine rotor and rotating the compressor,
an inter-turbine stator disposed between the first turbine and the second turbine, the inter-turbine stator comprising a plurality of arms extending between an inner end and an outer end, the plurality of arms extending through the primary annular flow path,
a cooling assembly comprising a first cooling circuit having successively:
a first cooling inlet located between the impeller and the compressor,
a first passage extending through the primary annular flow path into the inter-turbine stator from the inner end to the outer end, and
a first cooling outlet extending into the cold flow channel.