Turboreactor for aircraft
AssigneeAirbus Operations GmbH
InventorsGuillaume Bulin, Patrick Oberle
Life of this patent
Estimating the term…
Abstract
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.
Claims17
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.
An aircraft including at least one turbojet for the aircraft, the at least one turbojet including an engine located in a nacelle, the aircraft 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.
A turbojet engine for an aircraft comprising:
- a motor housed in a nacelle, wherein an internal wall of the nacelle and an external wall of the motor is at least partially covered with an acoustic coating;
- and
- a thermal exchanger adapted to cool a fluid participating in the propulsion system of the motor, wherein said thermal exchanger is located downstream from the acoustic coating and at a surface level of the external wall of the motor, 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 motor 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 motor external wall and the inner wall of said thermal exchanger.
Dependencies are inferred from the claim text.