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    TWO-TURBINE GEARED ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    2.
    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.

    Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections
    5.
    发明授权
    Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections 有权
    具有风扇连接导流段和多个低压涡轮段的燃气轮机

    公开(公告)号：US08915700B2

    公开(公告)日：2014-12-23

    申请号：US13407899

    申请日：2012-02-29

    申请人： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    发明人： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC分类号： F01D1/00

    CPC分类号： F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311

    摘要： A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

    摘要翻译： 燃气涡轮发动机包括限定旋转轴线的第一轴和能够围绕旋转轴线旋转并相对于第一轴径向向外间隔开的第二轴。 变速机构由第二轴驱动。 风扇包括由变速机构驱动的风扇转子，使得风扇和第一轴以比第二轴更慢的速度旋转。 至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

    GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING
    8.
    发明申请
    GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING 审中-公开
    具有三轮涡轮机的所有旋转齿轮

    公开(公告)号：US20130283819A1

    公开(公告)日：2013-10-31

    申请号：US13459498

    申请日：2012-04-30

    申请人： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Thomas J. Praisner

    发明人： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Thomas J. Praisner

    IPC分类号： F02C6/00

    CPC分类号： F02K3/06 ,  F02C7/36 ,  F05D2260/40311

    摘要： A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.

    摘要翻译： 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速滑阀，中速滑阀和风扇驱动涡轮机构造成沿相同的第一方向旋转。