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    INTEGRATED ENVIRONMENTAL CONTROL AND BUFFER AIR SYSTEM
    1.
    发明申请
    INTEGRATED ENVIRONMENTAL CONTROL AND BUFFER AIR SYSTEM 审中-公开

    公开(公告)号：US20170284305A1

    公开(公告)日：2017-10-05

    申请号：US15089806

    申请日：2016-04-04

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

    IPC: F02C9/18 ,  B64D13/06 ,  F02C7/32 ,  F02C3/04 ,  F02C7/06

    Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.

    Integrated environmental control and buffer air system
    2.
    发明授权
    Integrated environmental control and buffer air system 有权

    公开(公告)号：US10774752B2

    公开(公告)日：2020-09-15

    申请号：US15089806

    申请日：2016-04-04

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

    IPC: F02C9/00 ,  F02C9/18 ,  F02C3/04 ,  F02C7/06 ,  F02C7/32 ,  B64D13/06 ,  F02C6/08

    Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.

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