A thermal management system for one or more aircraft components includes a bleed airflow source at a gas turbine engine (20) of the aircraft, one or more turbines (68) configured to expand the bleed airflow, thus lowering a temperature of the bleed airflow, the bleed airflow driving rotation of the one or more turbines. One or more heat exchangers (70) are in fluid communication with the one or more turbines. The one or more heat exchangers are configured to exchange thermal energy between the bleed airflow and a thermal load. One or more electrical generators (94) are operably connected to the one or more turbines. The one or more electrical generators are configured to convert rotational energy of the one or more turbines to electrical energy.
THERMAL MANAGEMENT SYSTEM WITH COOLING TURBINE AND GENERATOR
WÄRMEVERWALTUNGSSYSTEM MIT KÜHLTURBINE UND GENERATOR
SYSTÈME DE GESTION THERMIQUE AVEC TURBINE DE REFROIDISSEMENT ET GÉNÉRATEUR
2023-05-03
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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