An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.


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    Titel :

    Engine bleed air system


    Beteiligte:
    BRUNO LOUIS J (Autor:in) / DEFRANCESCO GREGORY L (Autor:in) / ZYWIAK THOMAS M (Autor:in) / DREW DIANE G (Autor:in) / HIPSKY HAROLD W (Autor:in) / HUGHES DANIEL L (Autor:in)

    Erscheinungsdatum :

    28.04.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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