公开(公告)号：US20120301305A1

公开(公告)日：2012-11-29

申请号：US13116076

申请日：2011-05-26

Applicant: Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye

Inventor： Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye

IPC: F01D5/30

CPC classification number: F01D5/282 ,  F01D5/026 ,  F01D5/066 ,  F01D5/284 ,  F01D5/34 ,  F05D2300/6033

Abstract: A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.

Abstract translation: 用于燃气涡轮发动机的转子盘包括CMC轮毂和与CMC轮毂相对的多个CMC翼型件集成的轨道，轨道限定了轨道平台部分，该轨道平台部分向轨道内孔逐渐变细。

公开(公告)号：US20120288366A1

公开(公告)日：2012-11-15

申请号：US13294492

申请日：2011-11-11

Applicant: Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F01D25/28

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/12 ,  F05D2240/55

Abstract: A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.

Abstract translation: 用于燃气涡轮发动机的压缩机壳体支撑装置包括具有中心轴线的风扇部分和用于容纳压缩机的压缩机壳体。 入口箱将空气引导到压缩机。 压缩机壳体比入口箱更远离风扇部分。 支撑构件在风扇部分和压缩机壳体之间延伸。 支撑构件限制压缩机壳体相对于入口壳体的移动。 支撑构件比管道通路区域更远离风扇部分。

公开(公告)号：US08256707B2

公开(公告)日：2012-09-04

申请号：US11832107

申请日：2007-08-01

Applicant: Gabriel L. Suciu ,  Jon A. Marx ,  Brian D. Merry ,  Craig A. Nordeen ,  Christopher M. Dye

Inventor： Gabriel L. Suciu ,  Jon A. Marx ,  Brian D. Merry ,  Craig A. Nordeen ,  Christopher M. Dye

IPC: B64D27/00

CPC classification number: F02C7/20 ,  B64D27/18 ,  B64D27/26 ,  B64D2027/268 ,  Y02T50/44 ,  Y10T29/49826

Abstract: An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.

Abstract translation: 发动机安装配置可使发动机推力在后方安装。 发动机安装配置减少了发动机的主干弯曲，中间壳失真和内部机舱内的释放空间。

公开(公告)号：US20120167592A1

公开(公告)日：2012-07-05

申请号：US13414763

申请日：2012-03-08

Applicant: Gabriel L. Suciu ,  Brian D. Merry ,  David W.J. Franklin ,  Christopher M. Dye

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  David W.J. Franklin ,  Christopher M. Dye

IPC: F02C7/20

CPC classification number: B64D27/26 ,  B64D2027/266 ,  B64D2027/268

Abstract: A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine.

Abstract translation: 用于燃气涡轮发动机的安装系统包括安装连杆组件和大致横向于安装连杆组件定位的切向连杆。 安装联动装置至少起反推力。 切向连杆至少响应燃气涡轮发动机的垂直载荷，侧向载荷和扭矩载荷。

公开(公告)号：US08015798B2

公开(公告)日：2011-09-13

申请号：US11955630

申请日：2007-12-13

Applicant: James W. Norris ,  Brian D. Merry

Inventor： James W. Norris ,  Brian D. Merry

IPC: F02K3/00

CPC classification number: F02K3/072 ,  F02C3/067 ,  F02C3/107 ,  F05D2260/40 ,  F05D2260/4031 ,  Y02T50/671

Abstract: A gas turbine engine includes a gear system driven by a first and second counter rotating low pressure shaft and a fan driven by the gear system.

Abstract translation: 燃气涡轮发动机包括由第一和第二反向旋转低压轴驱动的齿轮系和由齿轮系驱动的风扇。

公开(公告)号：US20100242496A1

公开(公告)日：2010-09-30

申请号：US12413634

申请日：2009-03-30

Applicant: Michael F. Cass ,  James S. Elder ,  Brian D. Merry ,  Gabriel L. Suciu ,  Chritopher M. Dye

Inventor： Michael F. Cass ,  James S. Elder ,  Brian D. Merry ,  Gabriel L. Suciu ,  Chritopher M. Dye

IPC: F02C6/00 ,  F02C7/32

CPC classification number: F02C7/32 ,  Y02T50/671

Abstract: An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis.

Abstract translation: 用于燃气涡轮发动机的发动机附件系统包括沿附件轴线限定的第一附件部件和沿附件轴线安装到第一附件部件的第二附件部件。

公开(公告)号：US20090290976A1

公开(公告)日：2009-11-26

申请号：US12154200

申请日：2008-05-21

Applicant: Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye

IPC: F01D15/12

CPC classification number: F02C7/32 ,  F01D25/18 ,  F05D2260/403 ,  Y10T29/49464

Abstract: An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.

Abstract translation: 用于燃气涡轮发动机的组件包括中间壳体和变速箱。 中间壳体限定环形过渡管道。 齿轮箱包括多个叶片，并与环形过渡管道整体形成。

公开(公告)号：US20090081039A1

公开(公告)日：2009-03-26

申请号：US11860719

申请日：2007-09-25

Applicant: Michael E. McCune ,  Brian D. Merry ,  Gabriel L. Suciu

Inventor： Michael E. McCune ,  Brian D. Merry ,  Gabriel L. Suciu

IPC: F01D25/24

CPC classification number: F02C7/36 ,  F02C7/04 ,  F02K3/06 ,  F05D2230/60

Abstract: A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.

Abstract translation: 公开了一种燃气涡轮发动机，其包括具有压缩机部分的阀芯。 入口壳体在压缩机部分的轴向上游设置。 齿轮箱固定在入口箱上。 齿轮箱连接线轴和风扇。 密封组件布置在入口壳体和齿轮箱之间以提供密封的轴承隔室。 入口箱，齿轮箱和密封组件提供一个模块。 紧固元件将模块可拆卸地固定到线轴上。 燃气涡轮发动机可以通过将紧固元件与发动机芯断开来进行维修。 齿轮箱和进气口箱可以作为模块从发动机内芯上拆下，而不必拆卸变速箱。

公开(公告)号：US09938831B2

公开(公告)日：2018-04-10

申请号：US13283689

申请日：2011-10-28

Applicant: Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve ,  James W. Norris

IPC: F01D5/06 ,  F01D5/02

CPC classification number: F01D5/026 ,  F01D5/06 ,  F01D5/066

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.

公开(公告)号：US09816441B2

公开(公告)日：2017-11-14

申请号：US12413634

申请日：2009-03-30

Applicant: Michael F. Cass ,  James S. Elder ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

Inventor： Michael F. Cass ,  James S. Elder ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/32

CPC classification number: F02C7/32 ,  Y02T50/671

Abstract: An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis.