US 12,312,971 B2
Turbomachine for an aircraft
Nicolas Stoliaroff-Pepin, Moissy-Cramayel (FR); Julien Fabien Patrick Becoulet, Moissy-Cramayel (FR); Maeva Daphné Gros-Borot, Moissy-Cramayel (FR); and Paco Maurer, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/838,100
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Feb. 15, 2023, PCT No. PCT/FR2023/050200
§ 371(c)(1), (2) Date Aug. 13, 2024,
PCT Pub. No. WO2023/156733, PCT Pub. Date Aug. 24, 2023.
Claims priority of application No. 2201432 (FR), filed on Feb. 17, 2022.
Prior Publication US 2025/0146427 A1, May 8, 2025
Int. Cl. F01D 25/18 (2006.01); F01D 5/08 (2006.01); F01D 11/02 (2006.01); F01D 25/12 (2006.01); F01D 25/16 (2006.01); F01D 25/20 (2006.01); F02C 6/08 (2006.01); F02C 7/14 (2006.01); F02C 7/16 (2006.01); F02C 9/18 (2006.01); F02C 9/52 (2006.01)
CPC F01D 25/183 (2013.01) [F01D 5/08 (2013.01); F01D 5/085 (2013.01); F01D 11/02 (2013.01); F01D 25/12 (2013.01); F01D 25/125 (2013.01); F01D 25/16 (2013.01); F01D 25/18 (2013.01); F01D 25/20 (2013.01); F02C 6/08 (2013.01); F02C 7/14 (2013.01); F02C 7/16 (2013.01); F02C 9/18 (2013.01); F02C 9/52 (2013.01); F05D 2220/323 (2013.01); F05D 2240/54 (2013.01); F05D 2240/55 (2013.01); F05D 2260/98 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A turbomachine for an aircraft, the turbomachine extending along a longitudinal axis and comprising:
a low-pressure compressor comprising a compressor rotor,
a low-pressure shaft configured to drive the compressor rotor, the low-pressure shaft being centered on the longitudinal axis and having an internal passage configured for the circulation of a first air stream along the longitudinal axis from upstream to downstream, the low-pressure shaft comprising:
a first cylindrical segment,
a second segment secured in rotation to the first segment and arranged upstream of the first segment, the second segment comprising a first frustoconical portion connected to the compressor rotor,
an intermediate casing arranged around the first segment and downstream of the low-pressure compressor,
at least one bearing configured to guide the low-pressure shaft in rotation, arranged radially between the first segment and the intermediate casing,
an annular intermediate lubrication chamber wherein said at least one bearing is arranged, the intermediate lubrication chamber being arranged in the intermediate casing,
an annular air chamber configured to be supplied with air from the low-pressure compressor, the air chamber being delimited axially, at least in part, by the first frustoconical portion and a radial separating wall mounted around the first segment, the first frustoconical portion also having at least one opening putting the air chamber into communication with the internal passage to allow the first air stream to pass from the air chamber to the internal passage.