公开(公告)号：US20140230403A1

公开(公告)日：2014-08-21

申请号：US14012576

申请日：2013-08-28

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

IPC: F01D25/16 ,  F02K3/06 ,  F02C7/36

CPC classification number: F01D25/162 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  Y02T50/671

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 第一轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的低压压缩机部分。 第一轴承相对于入口壳体支撑第一轴。 第二轴承相对于中间壳体支撑第二轴。 低压压缩机毂安装在第一轴上。 低压压缩机毂在第一轴承和第二轴承之间延伸到低压压缩机部分。

公开(公告)号：US20140169972A1

公开(公告)日：2014-06-19

申请号：US13716959

申请日：2012-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

IPC: F01D5/22

CPC classification number: F01D5/225 ,  F01D5/34 ,  F01D21/045 ,  F04D29/023 ,  F04D29/321 ,  F05D2220/36 ,  F05D2230/53 ,  F05D2260/96 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672

Abstract: An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.

Abstract translation: 用于燃气涡轮发动机的整体叶片转子包括中心毂; 从中心毂延伸的多个翼型件，每个翼型件具有尖端，前缘和后缘; 以及具有连接到每个翼型件的尖端以与翼型件一起旋转的金属部分的护罩。

公开(公告)号：US08511061B1

公开(公告)日：2013-08-20

申请号：US13762970

申请日：2013-02-08

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L Suciu

IPC: F02K3/04

CPC classification number: F01D25/16 ,  F01D25/162 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  F05D2250/19 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.

Abstract translation: 燃气涡轮发动机包括具有入口壳体和中间壳体的芯壳体，其分别提供入口壳体流动路径和中间壳体流动路径。 轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的压缩机部分。 轴包括主轴和具有波纹管的挠性轴。 柔性轴在第一端处固定到主轴，并且包括与第一端相对的第二端。 齿轮架构耦合到轴，并且风扇耦合到由齿轮架构旋转地驱动。 齿轮架构包括在第二端支撑的太阳齿轮。 第一轴承相对于中间壳体支撑轴，第二轴承相对于入口壳体支撑轴。 第二轴承从柔性轴径向向外设置。