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    Gas turbine engine forward bearing compartment architecture
    13.
    发明授权
    Gas turbine engine forward bearing compartment architecture 有权

    公开(公告)号：US10465549B2

    公开(公告)日：2019-11-05

    申请号：US15865393

    申请日：2018-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Peter M. Munsell ,  Philip S. Stripinis

    IPC: F01D15/12 ,  F01D25/08 ,  F01D25/16 ,  F01D25/24 ,  F01D5/06 ,  F01D9/06 ,  F02C6/08 ,  F02C7/36 ,  F04D29/32

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a low pressure compressor, and a high pressure compressor axially aft of the low pressure compressor. A first case structure defines a core flow path for core airflow into the low pressure compressor and has a forward end and an aft end. A second case structure defines a core flow path for core airflow into the high pressure compressor and is mounted to the aft end of the first case structure. A geared architecture is at least partially supported by the first case structure. A first bearing structure is mounted to the first case structure to rotationally support a fan shaft that connects with the geared architecture to drive the fan. A flex support provides a flexible attachment of the geared architecture within the first case structure. A fan drive turbine drives the geared architecture to drive the fan at a speed lower than a speed of the fan drive turbine.

    COMPRESSED AIR BLEED SUPPLY FOR BUFFER SYSTEM
    14.
    发明申请
    COMPRESSED AIR BLEED SUPPLY FOR BUFFER SYSTEM 审中-公开

    公开(公告)号：US20180149088A1

    公开(公告)日：2018-05-31

    申请号：US15882058

    申请日：2018-01-29

    Applicant: United Technologies Corporation

    Inventor： Peter M. Munsell ,  Philip S. Stripinis

    IPC: F02C7/18 ,  F02C6/08 ,  F01D25/18 ,  F01D25/22

    Abstract: A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.

    COMPRESSED AIR BLEED SUPPLY FOR BUFFER SYSTEM
    17.
    发明申请
    COMPRESSED AIR BLEED SUPPLY FOR BUFFER SYSTEM 审中-公开
    用于缓冲系统的压缩空气供应

    公开(公告)号：US20140216004A1

    公开(公告)日：2014-08-07

    申请号：US14246260

    申请日：2014-04-07

    Applicant: United Technologies Corporation

    Inventor： Peter M. Munsell ,  Philip S. Stripinis

    IPC: F02C6/08 ,  F02C7/18

    CPC classification number: F02C7/18 ,  F01D25/183 ,  F01D25/22 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/675 ,  Y10T29/49359

    Abstract: A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet. The first outlet is configured to provide a cooled pressurized fluid. The buffer system includes first and second air sources that are selectively fluidly coupled to the first inlet, and a third air source that are fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include a bearing compartment. A method and a buffer system are also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇，流体连接到风扇的压缩机部分，与压缩机部分流体连接的燃烧器，流体连接到燃烧器的涡轮机部分和缓冲系统。 缓冲系统包括具有第一入口，第一出口，第二入口和第二出口的热交换器。 第一出口构造成提供冷却的加压流体。 缓冲系统包括选择性地流体耦合到第一入口的第一和第二空气源，以及流体地联接到第二入口的第三空气源。 多个流体供应区域彼此远离并且流体地联接到第一出口。 多个流体供应区域包括轴承室。 还公开了一种方法和缓冲系统。

    GAS TURBINE ENGINE BUFFER SYSTEM
    18.
    发明申请
    GAS TURBINE ENGINE BUFFER SYSTEM 审中-公开
    气体涡轮发动机缓冲系统

    公开(公告)号：US20140196470A1

    公开(公告)日：2014-07-17

    申请号：US14219070

    申请日：2014-03-19

    Applicant: United Technologies Corporation

    Inventor： Jorn A. Glahn ,  Clifton J. Crawley, JR. ,  Philip S. Stripinis ,  William K. Ackermann

    IPC: F02C9/18

    CPC classification number: F02C9/18 ,  F01D11/04 ,  F01D25/00 ,  F01D25/16 ,  F02C6/08 ,  F02C7/06 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F05D2260/601 ,  Y02T50/675 ,  Y10T29/49229

    Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.

    Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分，经由齿轮架构被涡轮部分驱动的风扇部分和缓冲系统， 将缓冲空气传送到燃气涡轮发动机的一部分。 缓冲系统包括第一回路，其被配置为选择性地混合具有第一压力的第一排气供应源和第二排气源，其具有大于第一压力的第二压力，以提供具有中压的第一缓冲器供应空气， 第一压力和第二压力。

    GAS TURBINE ENGINE BUFFER SYSTEM
    19.
    发明申请
    GAS TURBINE ENGINE BUFFER SYSTEM 审中-公开

    公开(公告)号：US20200263604A1

    公开(公告)日：2020-08-20

    申请号：US16677721

    申请日：2019-11-08

    Applicant: United Technologies Corporation

    Inventor： Peter M. Munsell ,  Philip S. Stripinis

    IPC: F02C6/08 ,  F01D11/06 ,  F01D25/12 ,  F01D11/04 ,  F02C9/18

    Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.

    Compressed air bleed supply for buffer system
    20.
    发明授权
    Compressed air bleed supply for buffer system 有权

    公开(公告)号：US09879602B2

    公开(公告)日：2018-01-30

    申请号：US14246260

    申请日：2014-04-07

    Applicant: United Technologies Corporation

    Inventor： Peter M. Munsell ,  Philip S. Stripinis

    IPC: F02C1/00 ,  F02C7/18 ,  F02C6/08 ,  F01D25/22 ,  F01D25/18

    CPC classification number: F02C7/18 ,  F01D25/183 ,  F01D25/22 ,  F02C6/08 ,  F02C7/185 ,  Y02T50/675 ,  Y10T29/49359

    Abstract: A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet. The first outlet is configured to provide a cooled pressurized fluid. The buffer system includes first and second air sources that are selectively fluidly coupled to the first inlet, and a third air source that are fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include a bearing compartment. A method and a buffer system are also disclosed.

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