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    TURBINE ENGINE CASE MOUNT AND DISMOUNT
    61.
    发明申请
    TURBINE ENGINE CASE MOUNT AND DISMOUNT 审中-公开
    涡轮发动机壳体安装和配置

    公开(公告)号：US20130232768A1

    公开(公告)日：2013-09-12

    申请号：US13417615

    申请日：2012-03-12

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Brian D. Merry

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Brian D. Merry

    IPC分类号： B23P17/04

    CPC分类号： F02C7/20 ,  B64D27/10 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/266 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/90 ,  Y02T50/44 ,  Y10T29/49947

    摘要： A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

    摘要翻译： 一种用于安装具有压缩机部分，燃烧器部分，涡轮机部分，塔架和后部安装支架的燃气涡轮发动机的方法，包括将安装支架定位在燃气涡轮发动机和塔架之间。 安装支架连接到涡轮机壳体，使至少垂直载荷，侧向载荷，推力载荷和来自燃气涡轮发动机的转矩载荷通过安装支架反应。 安装支架连接到塔架，使来自燃气涡轮发动机的相同负载反应。

    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO MID TURBINE FRAME
    62.
    发明申请
    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO MID TURBINE FRAME 有权
    具有安装在中间涡轮机框架上的齿轮系统的逆转低压涡轮机

    公开(公告)号：US20130219856A1

    公开(公告)日：2013-08-29

    申请号：US13408178

    申请日：2012-02-29

    申请人： Gabriel L. Suciu ,  Brian D. Merry

    发明人： Gabriel L. Suciu ,  Brian D. Merry

    IPC分类号： F02K3/072 ,  F02C3/107

    CPC分类号： F02C3/107 ,  F01D1/26 ,  F01D25/162 ,  F02C3/067 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2250/36 ,  F05D2250/44 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

    摘要： A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. The gear system is mounted to a mid-turbine frame.

    摘要翻译： 燃气涡轮发动机包括限定旋转轴线的轴。 外涡轮转子直接驱动轴并且包括外部一组叶片。 内部涡轮转子具有与外部组叶片交替散布的内部一组叶片。 内涡轮转子被构造成围绕与外涡轮转子的旋转轴线相反的方向旋转。 齿轮系将内涡轮转子与轴连接，并且构造成以比外套叶片更快的速度旋转内组叶片。 齿轮系统安装到中涡轮机架。

    Gas turbine engine compressor arrangement
    65.
    发明授权
    Gas turbine engine compressor arrangement 有权
    燃气涡轮发动机压缩机布置

    公开(公告)号：US08449247B1

    公开(公告)日：2013-05-28

    申请号：US13590273

    申请日：2012-08-21

    申请人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    发明人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC分类号： F01D1/00

    CPC分类号： F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

    摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas a pressure ratio across the fan section being less than or equal to about 1.45.

    摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而风扇部分的压力比小于或等于约1.45。

    GAS TURBINE ENGINE GENERATOR SWITCHABLE DRIVE
    68.
    发明申请
    GAS TURBINE ENGINE GENERATOR SWITCHABLE DRIVE 有权
    气体发动机发动机可切换驱动

    公开(公告)号：US20130047626A1

    公开(公告)日：2013-02-28

    申请号：US13218863

    申请日：2011-08-26

    申请人： Brian D. Merry ,  Gabriel L. Suciu

    发明人： Brian D. Merry ,  Gabriel L. Suciu

    IPC分类号： F02C7/275 ,  F02C7/26

    CPC分类号： F02C7/32 ,  F02C7/275 ,  F05D2220/76 ,  F05D2250/34 ,  F05D2250/41 ,  F05D2260/36 ,  F05D2260/4031

    摘要： A gas turbine engine includes a first spool, a first gear system connected to and driven by the first spool, a second spool, and a second gear system connected to and driven by the second spool. A first starter-generator has a first shaft with a switchable coupling connected to the first shaft. The switchable coupling selectively couples the first starter-generator to the first gear system when the switchable coupling is in a first position and selectively couples the first starter-generator to the second gear system when the switchable coupling is in a second position.

    摘要翻译： 燃气涡轮发动机包括第一阀芯，与第一阀芯连接并由第一阀芯驱动的第一齿轮系，第二阀芯和连接到第二阀芯并由第二阀芯驱动的第二齿轮系。 第一起动发电机具有第一轴，其具有连接到第一轴的可切换联轴器。 当可切换联轴器处于第一位置时，可切换联接器将第一起动发电机选择性地联接到第一齿轮系统，并且当可切换联轴器处于第二位置时，可选择性地将第一起动器发电机耦合到第二齿轮系统。

    Gas turbine engine compressor arrangement
    69.
    发明授权
    Gas turbine engine compressor arrangement 有权
    燃气涡轮发动机压缩机布置

    公开(公告)号：US08337149B1

    公开(公告)日：2012-12-25

    申请号：US13590399

    申请日：2012-08-21

    申请人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    发明人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC分类号： F01D1/00

    CPC分类号： F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

    摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45.

    摘要翻译： 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过所述低压压缩机部分上的压力比和所述高压压缩机部分之间的压力比的组合提供的总压力比大于约35.跨过高压压缩机部分的压力比介于约 7和15左右，风扇部分的压力比小于或等于1.45。