Heat exchanger for cooling an aircraft propulsion engine
AssigneeSogeclair SA
InventorAlexandre Boulzaguet
Life of this patent
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Abstract
The heat exchanger is generally ring-shaped and includes a plurality of heat exchange modules (2), which are mutually independent, being distributed about the axis (A1) of the ring. The modules (2) are assembled with one another, being successively spaced apart in pairs, a space (E1) being created between two adjacent modules (2). At least one of the spaces (E1) receives at least one conductive heat-transfer element (7) extending between respective walls of at least two adjacent the modules (2) which are oriented facing one another.
Claims16
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.
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;
- wherein each one of the at least one conductive heat-transfer elements (7) are received in said at least one and the same space (E1);
- and
- wherein since the ring has along its edge (T1) a variation in thickness (Ep1, Ep2) between its axial ends (5a, 5b), the number of heat-transfer elements (7) varies axially (A1) according to the variation in thickness (Ep1, Ep2) of the edge (T1) of the ring.
Dependencies are inferred from the claim text.