Turboreactor for aircraft

摘要

The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

主权项

1. A turbojet for an aircraft including an engine located in a nacelle the turbojet comprising:
a thermal exchanger adapted to cool a liquid participating in the engine propulsive system, wherein said thermal exchanger is located downstream from the nacelle and at a surface level of an external wall of the engine, an interstitial space being defined in a recess, the recess receiving the thermal exchanger in a disposition wherein air can circulate in the interstitial space between an engine external wall and an inner wall of said thermal exchanger, wherein the interstitial space is defined by an intake opening, adjoining a shallow in-slope portion, adjoining a steep in-slope portion, adjoining an arcuate bottom portion, adjoining a steep out-slope portion, adjoining a portion substantially parallel to the axis of the engine, adjoining a shallow out-slope portion, adjoining an exhaust opening, thereby creating a thermal resistance between the engine external wall and the inner wall of said thermal exchanger.