US 12,292,001 B2
Propulsive assembly for aircraft
Philippe Mogilka, Blagnac (FR); Lionel Czapla, Toulouse (FR); and Alexis Pissavin, Blagnac (FR)
Assigned to Airbus SAS, Blagnac (FR); and Airbus Operations SAS, Toulouse (FR)
Filed by Airbus SAS, Blagnac (FR); and Airbus Operations SAS, Toulouse (FR)
Filed on Sep. 28, 2023, as Appl. No. 18/476,586.
Claims priority of application No. 2209992 (FR), filed on Sep. 30, 2022.
Prior Publication US 2024/0109668 A1, Apr. 4, 2024
Int. Cl. F02C 7/22 (2006.01); B64D 37/30 (2006.01); F02C 3/20 (2006.01); F02C 3/22 (2006.01); B64D 27/12 (2006.01); B64D 29/02 (2006.01); B64D 29/08 (2006.01)
CPC F02C 7/222 (2013.01) [B64D 37/30 (2013.01); F02C 3/20 (2013.01); F02C 3/22 (2013.01); B64D 27/12 (2013.01); B64D 29/02 (2013.01); B64D 29/08 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A propulsive assembly for an aircraft comprising:
a nacelle composed of cowls,
an engine system housed in the nacelle and comprising a core enclosed in a casing and having a combustion chamber and a turbine provided with blades rotating about a longitudinal axis,
a supply line configured to convey dihydrogen and winding outside the casing to the rear of the turbine,
an injector manifold arranged around the casing and the combustion chamber and equipped with injectors which dip into the combustion chamber through the casing, and
a distribution network which comprises several bypass lines distributed angularly around the casing, a rear manifold fluidically connected to the supply line and to each bypass line and a front manifold fluidically connected to each bypass line and to the injector manifold,
wherein the rear manifold is at a rear of the turbine and the front manifold is at a front of the turbine.