A gas turbine engine for an aircraft is provided. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes a core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to and vertically beneath the core casings. The engine further includes a heatshield positioned between the one or more engine accessories and the core casings. The heatshield contains one or more ventilation holes for channelling convectively driven flows of ventilation air around the one or more engine accessories on engine shutdown.
GAS TURBINE ENGINE HEATSHIELD
GASTURBINENTRIEBWERKHITZESCHILD
ÉCRAN THERMIQUE DE MOTEUR À TURBINE À GAZ
2019-09-25
Patent
Elektronische Ressource
Englisch
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