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    Modifying a Gas Turbine Engine to Use a High Pressure Compressor as a Low Pressure Compressor
    94.
    发明申请
    Modifying a Gas Turbine Engine to Use a High Pressure Compressor as a Low Pressure Compressor 审中-公开
    修改燃气轮机使用高压压缩机作为低压压缩机

    公开(公告)号：US20160208689A1

    公开(公告)日：2016-07-21

    申请号：US14598269

    申请日：2015-01-16

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Brian D. Merry

    IPC: F02C3/10

    CPC classification number: F02C3/06 ,  F05D2230/80

    Abstract: A method comprises the steps of modifying an existing engine which includes a high pressure compressor driven by a high pressure turbine and a low pressure turbine to drive a low pressure compressor. The modifying step includes utilizing the high pressure compressor as a low pressure compressor in a modified gas turbine engine, and designing and incorporating a new high pressure compressor downstream of the low pressure compressor section in the modified engine, such that a portion of the design of the existing engine is utilized in the modified engine. A gas turbine engine is also disclosed.

    Abstract translation: 一种方法包括以下步骤：修改现有的发动机，其包括由高压涡轮机和低压涡轮机驱动的高压压缩机，以驱动低压压缩机。 修改步骤包括在改性燃气涡轮发动机中利用高压压缩机作为低压压缩机，以及在改进的发动机中设计和并入低压压缩机部分下游的新的高压压缩机，使得设计的一部分 现有的发动机用于改进的发动机。 还公开了一种燃气涡轮发动机。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    95.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    高旁路涡轮机涡轮部分

    公开(公告)号：US20150377124A1

    公开(公告)日：2015-12-31

    申请号：US14793795

    申请日：2015-07-08

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C3/107 ,  F02K3/02 ,  F01D5/06 ,  F01D9/04 ,  F01D25/24

    CPC classification number: F02C3/107 ,  F01D9/041 ,  F01D25/24 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311

    Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having a circumferential array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A bypass area ratio is between about 8.0 and about 20.0. A ratio of maximum gaspath radius along the fan drive turbine section to maximum radius of the fan is less than about 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between about 10 and about 170. The fan drive turbine section airfoil count being the total number of blade airfoils and vane airfoils of the fan drive turbine section.

    Abstract translation: 涡轮风扇发动机包括发动机壳体，通过发动机壳体的气路，具有圆周阵列的风扇叶片的风扇，与风扇流体连通的压缩机，与压缩机流体连通的燃烧器，以及与压缩机流体连通的涡轮机 燃烧器。 涡轮机具有风扇驱动涡轮机部分，具有3到6个叶片级。 减速机构将风扇驱动涡轮部分连接到风扇。 旁路面积比在约8.0和约20.0之间。 风扇驱动涡轮机部分的最大气路径半径与风扇的最大半径的比值小于约0.50。 涡轮机翼型计数与旁路面积比的比率在约10和约170之间。风扇驱动涡轮机翼型计数是风扇驱动涡轮机部分的叶片翼型和叶片翼型的总数。

    GAS TURBINE ENGINE WITH DISTRIBUTED FANS WITH DRIVE CONTROL
    96.
    发明申请
    GAS TURBINE ENGINE WITH DISTRIBUTED FANS WITH DRIVE CONTROL 审中-公开
    具有驱动控制的分布式风扇的气体涡轮发动机

    公开(公告)号：US20150361880A1

    公开(公告)日：2015-12-17

    申请号：US14600487

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler ,  Michael Winter ,  Michael E. McCune ,  William G. Sheridan

    IPC: F02C3/10 ,  F01D15/10

    CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C3/107 ,  F02K3/00 ,  F02K3/077

    Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括多个风扇转子。 气体发生器包括至少一个压缩机转子，至少一个气体发生器涡轮机转子，燃烧部分和在至少一个气体发生器涡轮机转子下游的风扇驱动涡轮机。 轴构造成由风扇驱动涡轮机驱动。 轴接合齿轮以驱动多个风扇转子。 系统控制提供给多个风扇转子的功率量。 还公开了一种操作燃气涡轮发动机的方法。

    GAS TURBINE ENGINE WITH COOLING SCHEME FOR DRIVE GEAR SYSTEM AND PITCH CONTROL
    97.
    发明申请
    GAS TURBINE ENGINE WITH COOLING SCHEME FOR DRIVE GEAR SYSTEM AND PITCH CONTROL 有权
    具有用于驱动齿轮系统和调节控制的冷却方案的燃气涡轮发动机

    公开(公告)号：US20150300265A1

    公开(公告)日：2015-10-22

    申请号：US14440953

    申请日：2013-02-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler

    IPC: F02C7/36

    CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/022 ,  F02C7/052 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/44 ,  F05D2260/20 ,  Y02T50/675

    Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

    Abstract translation: 燃气涡轮发动机包括外部机舱。 鼻锥在外部机舱的径向内侧间隔开。 鼻锥限定了用于引导外部空气流和内部空气流的颗粒分离器。 内部气流被引导通过压缩机的核心入口。 发动机还包括用于驱动至少一个螺旋桨的驱动齿轮系统。 可变桨距控制系统可以改变至少一个螺旋桨的桨距角。 一些外部气流被引导到驱动齿轮系统和俯仰控制系统中的至少一个。

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