SYSTEM FOR COOLING AND ADJUSTING THE TEMPERATURE OF APPARATUSES IN THE PROPULSION ASSEMBLY OF AN AIRCRAFT

The invention relates to a system for cooling and adjusting the temperature of apparatuses (10, 23) in the propulsion assembly (1) of an aircraft, that comprises first means (21) for heat exchange between lubrication circuits (22a, 22b) of at least two of said apparatuses and a heat-carrier fluid co...

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Bibliographische Detailangaben
Hauptverfasser:	PUGLIESE, STEPHANE, FABRE, CHRISTIAN, BULIN, GUILLAUME, OBERLE, PATRICK
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MECHANICAL ENGINEERING TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a system for cooling and adjusting the temperature of apparatuses (10, 23) in the propulsion assembly (1) of an aircraft, that comprises first means (21) for heat exchange between lubrication circuits (22a, 22b) of at least two of said apparatuses and a heat-carrier fluid contained in a closed circuit (24), a second means (25, 26) for heat exchange between the heat-carrier fluid and at least one coolant (27, 28), the first heat exchange means (21) being arranged locally at each of said apparatuses (10, 23), the second heat exchange means (25, 26) being remote from said first means (21), the closed circuit (24) extending between at least two of said apparatuses (10, 23) and said second means (25, 26). L'objet de l'invention est un système de refroidissement et de régulation en température d'équipements (10, 23) d'un ensemble propulsif (1) d'aéronef qui comporte des premiers moyens d'échange de chaleur (21) entre des circuits de lubrification (22a, 22b) d'au moins deux desdits équipements et un fluide caloporteur contenu dans un circuit fermé (24), des seconds moyens d'échange de chaleur (25, 26) entre le fluide caloporteur et au moins un fluide de refroidissement (27, 28), les premiers moyens d'échange de chaleur (21) étant disposés localement au niveau de chacun desdits équipements (10, 23), les seconds moyens d'échange de chaleur (25, 26) étant distants desdits premiers moyens (21), le circuit fermé (24) circulant entre au moins deux des équipements (10, 23) et lesdits seconds moyens (25, 26).