中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

313 records (took 0.033 seconds)

    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE
    1.
    发明申请
    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE 审中-公开
    超高压总成比例气体涡轮发动机

    公开(公告)号：WO2015105594A2

    公开(公告)日：2015-07-16

    申请号：PCT/US2014/067529

    申请日：2014-11-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  STAUBACH, Joseph Brent

    IPC: F02C3/04 ,  F02C3/06

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor.

    Abstract translation: 燃气涡轮发动机包括位于第二中间涡轮机的上游的第一涡轮机和位于第一和第二涡轮机下游的第三涡轮机。 一个风扇和三个压缩机，其上游的一个压缩机连接成与风扇转子一起旋转，第三个涡轮通过齿轮减速器驱动上游压缩机和风扇。 第二中间压缩机由第二中间涡轮转子驱动，第一和第二压缩机下游的第三压缩机由第一涡轮转子驱动。

    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE
    3.
    发明申请
    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE 审中-公开
    具有高压缩机出口温度的齿轮涡轮发动机

    公开(公告)号：WO2014055114A1

    公开(公告)日：2014-04-10

    申请号：PCT/US2013/030407

    申请日：2013-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  HASEL, Karl L.

    IPC: F02K3/04 ,  F02K3/00 ,  F01D9/02

    CPC classification number: F02C3/13 ,  F01D5/34 ,  F02K3/06 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000 °F and about 1500 °F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

    Abstract translation: 燃气涡轮发动机包括具有可围绕轴线旋转的多个风扇叶片的风扇和至少包括第一和第二压缩机部分的压缩机部分。 压缩机部分的平均出口温度在约1000°F至约1500°F之间。 发动机还包括与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    TURBOMACHINE THRUST BALANCING SYSTEM
    4.
    发明申请
    TURBOMACHINE THRUST BALANCING SYSTEM 审中-公开
    涡轮平衡平衡系统

    公开(公告)号：WO2014052601A1

    公开(公告)日：2014-04-03

    申请号：PCT/US2013/061935

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  SHERIDAN, William G.

    IPC: F02C7/06 ,  F01D25/16

    CPC classification number: F01D25/16 ,  F02C7/06 ,  F05D2240/52 ,  F05D2260/15

    Abstract: An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine.

    Abstract translation: 示例涡轮机推力平衡系统包括与涡轮联接的构件，用于从其转动旋转动力。 承载装置可旋转地支撑构件。 承载装置构造成抵消涡轮机产生的基本上所有的推力。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    6.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开

    公开(公告)号：WO2013158187A1

    公开(公告)日：2013-10-24

    申请号：PCT/US2013/023603

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC: F02K3/075

    CPC classification number: F02C7/06 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE
    7.
    发明申请
    GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE 审中-公开

    公开(公告)号：WO2013141934A3

    公开(公告)日：2013-09-26

    申请号：PCT/US2012/071946

    申请日：2012-12-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KOHLENBERG, Gregory A. ,  ZAMORA, Sean P. ,  SCHWARZ, Frederick M.

    IPC: F01D25/24

    Abstract: A nacelle assembly for a high-bypass gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, and a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan variable area nozzle operable to vary the fan nozzle exit area by about 20%.

    LIGHTWEIGHT FAN DRIVING TURBINE
    9.
    发明申请
    LIGHTWEIGHT FAN DRIVING TURBINE 审中-公开
    轻型风扇驱动涡轮

    公开(公告)号：WO2013130280A1

    公开(公告)日：2013-09-06

    申请号：PCT/US2013/026255

    申请日：2013-02-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard

    IPC: F04B17/00

    CPC classification number: F01D5/284 ,  F01D5/225 ,  F01D5/28 ,  F01D5/3007 ,  F05D2300/174 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A gas turbine engine includes a shaft defining an axis of rotation and a fan driving turbine configured to drive the shaft. The fan driving turbine comprises a plurality of stages that are spaced apart from each other along the axis. Each stage includes a turbine disk comprised of a disk material and a plurality of turbine blades comprised of a blade material. The disk material and the blade material for one of the plurality of stages is selected based on a location of the one stage relative to the other stages of the plurality of stages.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴和构造成驱动轴的风扇驱动涡轮机。 风扇驱动涡轮机包括沿轴线彼此间隔开的多个级。 每个阶段包括由圆盘材料和由叶片材料构成的多个涡轮叶片组成的涡轮盘。 基于一级相对于多级的其他级的位置来选择用于多级中的一级的盘材料和刀片材料。

    GEARED TURBOFAN WITH A GEARBOX AFT OF A FAN DRIVE TURBINE
    10.
    发明申请
    GEARED TURBOFAN WITH A GEARBOX AFT OF A FAN DRIVE TURBINE 审中-公开
    带齿轮箱风扇驱动涡轮机AFT的齿轮齿轮箱

    公开(公告)号：WO2015138030A3

    公开(公告)日：2015-09-17

    申请号：PCT/US2014/071037

    申请日：2014-12-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

    IPC: F02C7/36

    Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机包括构造成驱动风扇部的驱动涡轮机，连接到驱动涡轮机并位于驱动涡轮机的后部的变速机构以及驱动涡轮机的后部 风扇。 变速机构的输出连接到风扇。

Patent Agency Ranking