TURBOJET ENGINE NACELLE PROVIDED WITH A COOLING ASSEMBLY FOR COOLING A COMPONENT

TURBOJET ENGINE NACELLE PROVIDED WITH A COOLING ASSEMBLY FOR COOLING A COMPONENT

The invention relates to a turbojet engine nacelle component (23) cooling assembly (30), said assembly (30) comprising at least one composite wall (20) separating a cold zone (8) and a hot zone (16) containing said component (23), said assembly (30) comprising at least one opening (31) made in said...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: THOUEMENT JEAN-FRANCOIS, MER PASCAL
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:The invention relates to a turbojet engine nacelle component (23) cooling assembly (30), said assembly (30) comprising at least one composite wall (20) separating a cold zone (8) and a hot zone (16) containing said component (23), said assembly (30) comprising at least one opening (31) made in said composite wall (20) and a thermally conductive interface element (33) positioned on the composite wall (20) in such a way as to obstruct said opening or openings (31), said element (33) being intended to be associated with said component (23). The invention also relates to a nacelle comprising a component (23) that is intended to be cooled, and to such a cooling assembly (30).