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    GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME
    4.
    发明申请
    GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME 有权
    气体涡轮发动机及其装配方法

    公开(公告)号：US20160146115A1

    公开(公告)日：2016-05-26

    申请号：US14919825

    申请日：2015-10-22

    申请人： General Electric Company

    发明人： Kurt David Murrow ,  Andrew Breeze-Stringfellow ,  Randy M. Vondrell ,  Tsuguji Nakano ,  Jeffrey Anthony Hamel ,  Darek Tomasz Zatorski

    IPC分类号： F02C9/20 ,  F02C7/042 ,  F02C9/18 ,  F02C3/04

    CPC分类号： F02C9/20 ,  F01D7/00 ,  F01D15/12 ,  F01D17/085 ,  F01D17/105 ,  F01D17/162 ,  F02C3/04 ,  F02C3/13 ,  F02C7/042 ,  F02C7/36 ,  F02C9/18 ,  F02K1/66 ,  F02K3/04 ,  F02K3/075 ,  F05D2220/36 ,  F05D2270/101 ,  F05D2270/303 ,  F05D2300/30 ,  Y02T50/672

    摘要： A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.

    摘要翻译： 提供了一种涡轮风扇燃气涡轮发动机系统的方法和系统。 燃气涡轮发动机系统包括耦合到第一可旋转轴的变桨距风扇（VPF）组件和耦合到第二可旋转轴的低压压缩机LPC。 LPC包括多个可变桨距定子叶片，其与LPC的转子的叶片行相互指向。 燃气涡轮发动机系统还包括联接到所述第一可旋转轴和所述第二可旋转轴的减速装置。 燃气涡轮发动机系统还包括位于所述LPC的出口和旁路管道之间的调节压力释放阀，以及被配置为响应于操作来调度所述多个变桨距定子叶片和所述调节压力释放阀的位置的控制器 所述涡轮风扇燃气涡轮发动机系统的状态和与所述LPC相关联的温度。

    HIGH FAN TIP SPEED ENGINE
    6.
    发明申请
    HIGH FAN TIP SPEED ENGINE 有权

    公开(公告)号：US20230028503A1

    公开(公告)日：2023-01-26

    申请号：US17384999

    申请日：2021-07-26

    申请人： General Electric Company

    发明人： Arthur William Sibbach ,  Brandon Wayne Miller ,  Christopher James Kroger ,  Jeffrey Donald Clements ,  Sean Christopher Binion ,  Tsuguji Nakano

    IPC分类号： F02C7/36 ,  F02K3/06

    摘要： A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of rotatable fan blades, each fan blade defining a fan tip speed; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and a gear box, wherein the turbomachine is operably coupled to the fan through the gear box, wherein a gear ratio of the gear box is greater than or equal to 1.2 and less than or equal to 3.0; wherein during operation of the turbofan engine at a rated speed the fan tip speed is greater than or equal to 1000 feet per second. In exemplary embodiments, during operation of the turbofan engine at the rated speed the fan pressure ratio is less than or equal to about 1.5.

    Gas turbine engine with inlet pre-swirl features
    7.
    发明授权
    Gas turbine engine with inlet pre-swirl features 有权

    公开(公告)号：US11480063B1

    公开(公告)日：2022-10-25

    申请号：US17485706

    申请日：2021-09-27

    申请人： General Electric Company

    发明人： Brandon Wayne Miller ,  Tsuguji Nakano

    IPC分类号： F01D9/04 ,  F01D17/14

    摘要： A gas turbine engine may include a fan, a plurality of inlet pre-swirl features disposed upstream of a fan, and an outlet guide vane assembly disposed downstream of the fan. The outlet guide vane assembly includes a plurality of outlet guide vanes that may define an outlet guide vane solidity profile, wherein the outlet guide vane solidity profile is achieves a minimum solidity at a radial position between an inner boundary and seventy percent of an outlet guide vane span. The fan includes a plurality of fan blades that may define a fan solidity profile, wherein the fan solidity profile maintains a solidity of greater than 1.1 between a radial position at seventy percent of the fan blade span and an outer boundary.

    Compressor endwall treatment to delay compressor stall
    10.
    发明授权
    Compressor endwall treatment to delay compressor stall 有权

    公开(公告)号：US10132323B2

    公开(公告)日：2018-11-20

    申请号：US14870300

    申请日：2015-09-30

    申请人： General Electric Company

    发明人： Swati Saxena ,  Andrew Breeze-Stringfellow ,  Rajkeshar Vijayraj Singh ,  Tsuguji Nakano

    IPC分类号： F04D27/02 ,  F02C3/04

    摘要： A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.