Patent ID: 8235657
Filing Date: 2012-08-07
Classification: F01D,F02C,F02K,F28D,Y02T

Abstract:
1. A turbojet for aircraft comprising: an engine housed in a nacelle; and a thermal exchanger designed to cool a hot fluid tapped in the propulsion system of the turbojet before the re-injection of said fluid, partially cooled, into said propulsion system, and an acoustic lining at least partially covering an internal wall of at least one of the nacelle or an external wall of the engine, wherein; the thermal exchanger is disposed in an internal volume of the nacelle, at a distance from the internal wall of the nacelle and the external wall of the engine, in such a way as to present at least two thermal exchange surfaces in the flow of a cold air stream going through the nacelle, the thermal exchanger is fixedly joined to the nacelle and the engine by longitudinal bifurcation and radial guiding blades, and internal volume of the thermal exchanger is divided into compartments selectable to adapt a volume of the thermal exchanger in which the fluid to be cooled flows to an available volume of the fluid to be cooled.