Processo de gerenciamento dos efluentes térmicos de uma aernave, dispositivo de resfriamento de uma aeronave e aeronave

A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a r...

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Bibliographische Detailangaben
Hauptverfasser:	JAN DITTMAR, GUILLAUME BULIN
Format:	Patent
Sprache:	por
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS 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 LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating-at the level of at least one propulsion system (112)-the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).