US 11,987,369 B2
Turbomachine with unducted dual propellers
Nicolas Jérôme Jean Tantot, Moissy-Cramayel (FR); Anthony Binder, Moissy-Cramayel (FR); and Mario Antoine Lambey, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/288,206
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 25, 2019, PCT No. PCT/FR2019/052557
§ 371(c)(1), (2) Date Apr. 23, 2021,
PCT Pub. No. WO2020/084271, PCT Pub. Date Apr. 30, 2020.
Claims priority of application No. 1859925 (FR), filed on Oct. 26, 2018.
Prior Publication US 2021/0403169 A1, Dec. 30, 2021
Int. Cl. B64D 27/10 (2006.01); B64C 11/30 (2006.01); B64C 11/48 (2006.01); B64D 27/24 (2006.01); F02B 61/04 (2006.01); F02C 3/067 (2006.01); F02C 7/36 (2006.01); B64D 27/00 (2006.01); B64D 27/02 (2006.01)
CPC B64D 27/10 (2013.01) [B64C 11/306 (2013.01); B64C 11/48 (2013.01); B64D 27/24 (2013.01); F02B 61/04 (2013.01); F02C 3/067 (2013.01); F02C 7/36 (2013.01); B64D 2027/005 (2013.01); B64D 2027/026 (2013.01); F05D 2220/324 (2013.01); F05D 2220/325 (2013.01); F05D 2220/76 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbomachine of an aircraft,
the turbomachine comprising:
an inner hub,
a low-pressure shaft,
a low pressure turbine configured to rotationally drive the low-pressure shaft,
an outer casing delimiting with the inner hub a flow path of a gas stream in which is disposed the low-pressure turbine, and
an electric motor/generator,
a first propeller, having a first axis of shimming, configured to be rotationally driven by the low-pressure shaft; and
a second propeller, having a second axis of shimming, downstream of and coaxial with the first propeller, and configured to be rotationally driven by the electric motor/generator,
the second propeller being disposed at a distance between 1.5 and 4 cord lengths from the first propeller, the distance being defined between the respective axes of shimming of each of the first and second propellers using a cord length of the first propeller.