US 12,188,412 B2
Heat exchanger for cooling an aircraft propulsion engine
Alexandre Boulzaguet, Toulouse (FR)
Assigned to SOGECLAIR SA, Blagnac (FR)
Appl. No. 17/619,996
Filed by SOGECLAIR SA, Blagnac (FR)
PCT Filed Jun. 15, 2020, PCT No. PCT/EP2020/025284
§ 371(c)(1), (2) Date Dec. 16, 2021,
PCT Pub. No. WO2020/253990, PCT Pub. Date Dec. 24, 2020.
Claims priority of application No. 1906469 (FR), filed on Jun. 17, 2019.
Prior Publication US 2022/0356843 A1, Nov. 10, 2022
Int. Cl. F02C 7/14 (2006.01); F28D 7/16 (2006.01); F28D 9/00 (2006.01); F28D 19/04 (2006.01); F28F 3/08 (2006.01); F28F 13/08 (2006.01)
CPC F02C 7/14 (2013.01) [F28D 7/1669 (2013.01); F28F 13/08 (2013.01); F28D 9/0012 (2013.01); F28D 19/044 (2013.01); F28F 3/08 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A heat exchanger (1) for cooling an aircraft propulsion engine, the heat exchanger (1) having a ring-shape and comprising:
a plurality of heat exchange modules (2) which are mutually independent and being distributed circumferentially about the axis (A1) of the ring,
said modules (2) being assembled with one another and being successively spaced apart in pairs,
each module comprising:
a first set of channels (3a) for the circulation of the air flow (F1b) generated by the advancing aircraft;
a second set of channels (3b) for the circulation of cooling fluid,
wherein a space (E1) traversed by the air flows (F1a) generated by the advancing aircraft is created between two adjacent modules (2), at least one of said spaces (E1) receiving at least one conductive heat-transfer element (7) extending between respective walls (4) of at least two adjacent said modules (2) which are oriented facing one another; and
wherein said at least one space (E1) is closed by an external cover (9a) and an internal cover (9b) of the ring, which are respectively created on the external face (6a) and the internal face (6b) of the ring.