The invention refers to an aircraft incorporating a bleed system adapted for extracting compressed air from the aircraft main engines (2) to be used as a source of pressurized air for the aircraft. The bleed air system comprises: a first pre-cooler (8) installed at one of the main engines nacelle and coupled with the bleed duct (1), and adapted for cooling down the bleed air extracted from the main engine (2); and a second pre-cooler (9) installed at the pylon (3) and coupled with bleed duct (1) and downstream the first pre-cooler (8). The working temperature of the aircraft bleed system is reduced, down to max 200 °C, so that the dimensions of an Over Heat Detection System (OHDS) is reduced.


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    Title :

    AIRCRAFT INCORPORATING A LOW-TEMPERATURE BLEED SYSTEM


    Additional title:

    FLUGZEUG MIT EINEM NIEDRIGTEMPERATURENTLÜFTUNGSSYSTEM
    AÉRONEF INTÉGRANT UN SYSTÈME DE PURGE À BASSE TEMPÉRATURE



    Publication date :

    2020-01-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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