US 12,228,035 B2
Hybrid turbofan engine for an aircraft, comprising a motor/generator cooled by heat pipes
Thierry Sibilli, Moissy-Cramayel (FR); Vincent François Georges Millier, Moissy-Cramayel (FR); and Loïc Paul Yves Guillotel, Moissy-Cramayel (FR)
Assigned to SAFRAN, Paris (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/261,443
Filed by SAFRAN, Paris (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 7, 2022, PCT No. PCT/FR2022/050048
§ 371(c)(1), (2) Date Oct. 10, 2023,
PCT Pub. No. WO2022/152998, PCT Pub. Date Jul. 21, 2022.
Claims priority of application No. 2100373 (FR), filed on Jan. 15, 2021.
Prior Publication US 2024/0068377 A1, Feb. 29, 2024
Int. Cl. F01D 15/10 (2006.01); B64D 27/24 (2006.01); F02C 7/12 (2006.01); F02K 3/115 (2006.01); B64D 27/02 (2006.01); F01D 9/04 (2006.01); F02K 3/06 (2006.01)
CPC F01D 15/10 (2013.01) [B64D 27/24 (2013.01); F02C 7/12 (2013.01); F02K 3/115 (2013.01); B64D 27/026 (2024.01); F01D 9/041 (2013.01); F02K 3/06 (2013.01); F05D 2260/208 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A hybrid turbine engine for an aircraft, comprising a fan, an electric generator/motor, and a gas generator comprising a combustion chamber, the hybrid turbine engine being designed so that the rotation of the fan is ensured by the electric generator/motor and/or by the gas generator, the hybrid turbine engine comprising a flow splitter nozzle from which extend, downstream, a primary flow path equipped at an inlet of the primary flow path with inlet guide vanes, and a secondary flow path equipped with outlet guide vanes, the hybrid turbine engine comprising, between the fan and the flow splitter nozzle, an inner boundary wall of an air flow path, located upstream of the inlet guide vanes of the primary flow path, and also comprising, upstream of the outlet guide vanes, an inner upstream boundary wall of the secondary flow path, the electric generator/motor including a rotor, and a stator carried by a stator support fastened to a stator portion of the hybrid turbine engine,
wherein the hybrid turbine engine further includes a plurality of heat pipes for cooling the electric generator/motor, each heat pipe including an evaporator section fastened on the stator support of the electric generator/motor, as well as a condensation section fastened on the inner boundary wall of the air flow path or on the inner upstream boundary wall of the secondary flow path, each heat pipe being in the form of a tube whose opposite end portions are respectively formed by the condensation section and by the evaporation section,
wherein the stator is radially outward from the rotor and the heat pipes are radially outward from the stator.