CABIN BLOWER SYSTEM
    1.
    发明申请
    CABIN BLOWER SYSTEM 审中-公开
    客舱喷淋系统

    公开(公告)号:US20160167789A1

    公开(公告)日:2016-06-16

    申请号:US14957972

    申请日:2015-12-03

    Abstract: An aircraft cabin blower system comprising a transmission and a compressor is disclosed. The system has a forward configuration in which the compressor is drivable in use via the transmission. The transmission comprises a toroidal continuously variable transmission giving selectively variable control over the rate at which the compressor is driven.

    Abstract translation: 公开了一种包括变速器和压缩机的飞机机舱鼓风机系统。 该系统具有正向构造,其中压缩机经由变速器在使用中是可驱动的。 变速器包括环形无级变速器,其给出对压缩机被驱动的速率的选择性可变的控制。

    GAS TURBINE ENGINE
    3.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号:US20170370284A1

    公开(公告)日:2017-12-28

    申请号:US15602429

    申请日:2017-05-23

    Abstract: A gas turbine engine (10) comprises: a low pressure compressor (18) comprising a centrifugal compressor stage (24); a low pressure turbine (44) configured to drive a load (12), the low pressure turbine (44) being provided rearwardly of the low pressure compressor (18); a high pressure turbine (42) provided rearwardly of the low pressure turbine (44); a combustor (40) provided rearwardly of the high pressure turbine (42); a high pressure compressor (32) provided rearwardly of the combustor (40); and an intercooler heat exchanger (28) configured to exchange heat between core airflow (B) exiting the low pressure compressor (18) and fan airflow (A), wherein the high pressure turbine (42) and high pressure compressor (32) are coupled by a high pressure shaft (46), and the low pressure turbine (44), low pressure compressor (18) and load (12) are coupled by a low pressure shaft (22).

    GAS TURBINE ENGINE
    5.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号:US20200224554A1

    公开(公告)日:2020-07-16

    申请号:US16720068

    申请日:2019-12-19

    Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.

    CABIN BLOWER SYSTEM
    7.
    发明申请
    CABIN BLOWER SYSTEM 审中-公开

    公开(公告)号:US20190233125A1

    公开(公告)日:2019-08-01

    申请号:US16239338

    申请日:2019-01-03

    Abstract: An aircraft cabin blower system includes a transmission configured to receive mechanical power from a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and power management system, wherein, when operating in a blower mode, the first electrical receives mechanical power from the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine acts as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system. The transmission's output drives a cabin blower compressor when operating in the blower mode, a speed of the output of the transmission being determined by a function of a speed of the first and second transmission inputs.

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