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    TWO-TURBINE GEARED ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    1.
    发明申请
    TWO-TURBINE GEARED ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 审中-公开

    公开(公告)号：US20190003382A1

    公开(公告)日：2019-01-03

    申请号：US15932447

    申请日：2014-06-27

    申请人： Frederick M. Schwarz ,  Gabriel L. Suciu

    发明人： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC分类号： F02C6/08 ,  B64D13/06 ,  F04D27/00 ,  F01D21/02

    摘要： A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and 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. The pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed.

    Buffer cooling system providing gas turbine engine architecture cooling
    4.
    发明授权
    Buffer cooling system providing gas turbine engine architecture cooling 有权
    缓冲冷却系统提供燃气轮机发动机架构冷却

    公开(公告)号：US09157325B2

    公开(公告)日：2015-10-13

    申请号：US13405502

    申请日：2012-02-27

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    IPC分类号： F02C6/08 ,  F01D5/08 ,  F02C7/06 ,  F02C7/18

    CPC分类号： F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

    摘要： A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

    摘要翻译： 燃气涡轮发动机包括具有第一热交换器，第一通道，第二通道和第三通道的缓冲冷却系统。 第一热交换器与放气气流交换热量以提供调节气流。 第一通道将调节气流的第一部分与燃气涡轮发动机的高压压缩机连通，第二通道将调节气流的第二部分连通到燃气涡轮发动机的高压涡轮机，并且第三通道 调节气流的第三部分到燃气涡轮发动机的低压涡轮机。