A single-piece gas turbine engine bleed duct for a gas turbine engine including: a main airflow conduit configured to transmit a bleed flow to a location outside the gas turbine engine; a pressure regulating valve for regulating airflow through the main airflow conduit; a first inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the first inlet duct including a non-return valve; and a second inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the second inlet duct including a control valve; wherein each of the first and second inlet ducts are directly connectable to an engine casing of a gas turbine engine.
GAS TURBINE ENGINE BLEED DUCT
2020-09-17
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS
European Patent Office | 2023
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