利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

324 条记录 (耗时 0.032 秒)

    Low Profile Compressor Bleed Air-Oil Coolers
    154.
    发明申请
    Low Profile Compressor Bleed Air-Oil Coolers 有权
    薄型压缩机排风机油冷却器

    公开(公告)号：US20140096534A1

    公开(公告)日：2014-04-10

    申请号：US13645067

    申请日：2012-10-04

    申请人： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford ,  Allan R. Penda

    发明人： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford ,  Allan R. Penda

    IPC分类号： F02C7/18 ,  F02C6/08

    CPC分类号： F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    摘要： An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    摘要翻译： 公开了一种用于燃气涡轮发动机的空气 - 油冷却器（AOC）。 AOC可以包括进油口，出油口以及进油口和出油口之间的热交换元件。 AOC可以纵向定位在发动机的风扇和V形槽之间，并且在低压压缩机和低压压缩机面板之间径向间隔开。 公开了一种包括AOC的燃气涡轮发动机。 发动机的AOC可以包括进油口，出油口和进油口和出油口之间的热交换元件。 发动机的AOC可以纵向地定位在发动机的风扇和V形槽之间，并且在低压压缩机和低压压缩机板之间径向间隔开。 还公开了一种操作用于燃气涡轮发动机的AOC的方法。

    GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY
    157.
    发明申请
    GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY 审中-公开
    用于改进扭矩密度的齿轮涡轮机结构

    公开(公告)号：US20130219908A1

    公开(公告)日：2013-08-29

    申请号：US13483406

    申请日：2012-05-30

    申请人： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu

    发明人： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu

    IPC分类号： F02C3/10

    CPC分类号： F01D25/162 ,  F02C3/107 ,  F02K3/072 ,  F05D2260/40311

    摘要： A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

    摘要翻译： 涡轮发动机包括风扇，具有低压压缩机部分和高压压缩机部分的压缩机部分，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。 涡轮部分包括低压涡轮部分和高压涡轮部分。 低压压缩机部分，低压涡轮部分和风扇沿第一方向旋转，而高压压缩机部分和高压涡轮部分沿与第一方向相反的第二方向旋转。

    Bearing mounting system in a low pressure turbine
    158.
    发明授权
    Bearing mounting system in a low pressure turbine 有权

    公开(公告)号：US08511986B2

    公开(公告)日：2013-08-20

    申请号：US12001130

    申请日：2007-12-10

    申请人： Ioannis Alvanos ,  Gabriel L. Suciu

    发明人： Ioannis Alvanos ,  Gabriel L. Suciu

    IPC分类号： F04D29/04

    CPC分类号： F02C7/06 ,  F01D25/16 ,  F05D2220/321 ,  Y02T50/671

    摘要： A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT
    159.
    发明申请
    GAS TURBINE ENGINE WITH SEPARATE CORE AND PROPULSION UNIT 有权
    具有独立核心和推进单元的气体涡轮发动机

    公开(公告)号：US20130205752A1

    公开(公告)日：2013-08-15

    申请号：US13370750

    申请日：2012-02-10

    申请人： Gabriel L. Suciu ,  Wesley K. Lord ,  Christopher M. Dye

    发明人： Gabriel L. Suciu ,  Wesley K. Lord ,  Christopher M. Dye

    IPC分类号： F02K3/02

    CPC分类号： F02C3/145 ,  F02C7/36 ,  F02K3/025 ,  F05D2250/314

    摘要： A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.

    摘要翻译： 燃气涡轮发动机包括安装成围绕第一轴线旋转的推进单元和安装成围绕第二轴线旋转的核心发动机，并且其中第一和第二轴线是不平行的。 燃气涡轮发动机包括由与推进单元相邻的自由涡轮机驱动的推进单元和相关联的风扇，并且具有包括压缩机，燃烧器和涡轮机部分的气体发生器核心发动机。 还公开了一种方法。