Nacelle of an aircraft engine, comprising an improved heat exchanger
AssigneeAirbus Operations GmbH
InventorChristian Flemin
Life of this patent
Estimating the term…
Abstract
An aircraft engine nacelle in which the inner fixed structure has a heat exchanger which is filled with a two-phase heat transfer fluid and which comprises a tube forming a loop with front, rear, lower and upper strands, and also a first complementary strand between the central zones of the front strand and of the upper strand, a second complementary strand between the central zones of the front strand and of the lower strand, a third complementary strand between the central zones of the rear strand and of the upper strand, and a fourth complementary strand between the central zones of the rear strand and of the lower strand.
Claims7
A nacelle for an engine of an aircraft, the nacelle comprising:
- an inner fixed structure which has two inner cowls and, for each inner cowl, a heat exchanger in which a two-phase heat transfer fluid circulates and which is secured to said inner cowl, wherein the heat exchanger comprises:
- a tube which forms a loop with a front strand, a rear strand, a lower strand and an upper strand,
- an evaporator zone located on the rear strand,
- a first complementary strand which fluidically connects a central zone of the front strand to a central zone of the upper strand,
- a second complementary strand which fluidically connects the central zone of the front strand to a central zone of the lower strand,
- a third complementary strand which fluidically connects a central zone of the rear strand to the central zone of the upper strand, and
- a fourth complementary strand which fluidically connects the central zone of the rear strand to the central zone of the lower strand.
Dependencies are inferred from the claim text.