US 11,692,453 B2
Aircraft turbine engine equipped with an electrical machine
Gilles Alain Marie Charier, Moissy-Cramayel (FR); Caroline Marie Frantz, Moissy-Cramayel (FR); Loïc Paul Yves Guillotel, Moissy-Cramayel (FR); and Vincent François Georges Millier, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/287,072
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 22, 2019, PCT No. PCT/FR2019/052500
§ 371(c)(1), (2) Date Apr. 20, 2021,
PCT Pub. No. WO2020/084241, PCT Pub. Date Apr. 30, 2020.
Claims priority of application No. 1859942 (FR), filed on Oct. 26, 2018.
Prior Publication US 2021/0355840 A1, Nov. 18, 2021
Int. Cl. F01D 15/10 (2006.01); F02C 7/32 (2006.01); F02K 3/06 (2006.01); H02K 7/18 (2006.01); H02K 9/14 (2006.01)
CPC F01D 15/10 (2013.01) [F02C 7/32 (2013.01); F02K 3/06 (2013.01); H02K 7/1823 (2013.01); H02K 9/14 (2013.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01); F05D 2260/232 (2013.01); F05D 2260/30 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An aircraft turbine engine comprising:
a gas generator;
a fan arranged upstream from the gas generator and configured to generate a main gas flow, one part of which flows into a duct of the gas generator to form a primary flow, and another part of which flows in a duct around the gas generator to form a secondary flow, the gas generator comprising a low-pressure body that comprises a rotor for driving the fan via a mechanical reduction gear;
an electrical machine mounted coaxially downstream of the reduction gear and upstream of an intermediate casing, the electrical machine including a rotor rotated by the rotor of the low-pressure body, and a stator, having an upstream end and a downstream end, extending around the rotor of the electrical machine;
a first annular shroud, which is surrounded by a second annular shroud, the first and second shrouds delimiting between them a portion of said duct of the primary flow wherein the first annular shroud is mounted around the electrical machine and extending directly around the stator of the electrical machine and wherein, between the upstream end and the downstream end, the stator abuts a radially inner surface of the first annular shroud, so that the first annular shroud has its radially outer surface swept by the primary flow of gases so as to cool said stator with aid of the primary flow.