公开(公告)号：US20160010552A1

公开(公告)日：2016-01-14

申请号：US14771038

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F01D25/12

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, a turbine section, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said turbine section.

Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块，涡轮部分和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和所述涡轮部分连通。

公开(公告)号：US20150377073A1

公开(公告)日：2015-12-31

申请号：US14769801

申请日：2014-02-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Gopal Das ,  Ioannis Alvanos ,  Brian D. Merry

IPC: F01D25/30 ,  F02C3/04 ,  B23K31/02 ,  B21K7/12

CPC classification number: F01D25/30 ,  B21K7/12 ,  B23K31/02 ,  F01D25/162 ,  F02C3/04 ,  F02C7/20 ,  F02K1/78 ,  F05D2220/30 ,  F05D2230/236 ,  F05D2230/25 ,  F05D2230/60 ,  F05D2300/174 ,  Y02T50/672

Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.

Abstract translation: 用于燃气涡轮发动机的涡轮机排气箱包括在CMC核心机舱后部和CMC尾锥之间的多个CMC涡轮机排气外壳支柱。

公开(公告)号：US20150361879A1

公开(公告)日：2015-12-17

申请号：US14600304

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Alan H. Epstein ,  Wesley K. Lord ,  Jesse M. Chandler ,  Stephen G. Pixton

IPC: F02C3/10 ,  B64D33/02 ,  B64D33/04 ,  F02K1/54 ,  B64D27/12

CPC classification number: F02C3/10 ,  B64D27/12 ,  B64D35/04 ,  F02C6/206 ,  F02C7/36 ,  F02K1/54

Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.

Abstract translation: 飞机主体包括支撑结构。 燃气涡轮发动机包括具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分的气体发生器。 风扇驱动涡轮机位于至少一个气体发生器涡轮转子的下游，并且构造成驱动轴。 轴接合齿轮以驱动多个风扇转子。 燃气涡轮发动机被嵌入到支撑结构中，使得有一个入口通过支撑结构通向风扇转子，以将空气输送到风扇转子。 还公开了一种燃气涡轮发动机。

公开(公告)号：US20150354822A1

公开(公告)日：2015-12-10

申请号：US14728991

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F23R3/10 ,  F02C3/04

CPC classification number: F23R3/10 ,  F01D5/082 ,  F01D9/06 ,  F01D25/125 ,  F02C3/04 ,  F02C6/08 ,  F02C7/185 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/303 ,  F05D2270/3062 ,  Y02T50/676

Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.

Abstract translation: 一种用于燃气涡轮发动机的涡轮喷射系统包括可操作以从热交换器接收空气的第一端，可操作以将混合冷却空气分配到涡轮级的第二端，在所述第一端下游的开口和在所述第一端下游的混合增压室 第一端和开口。 开口提供到所述涡轮喷射系统的直接流体通路。

公开(公告)号：US09194329B2

公开(公告)日：2015-11-24

申请号：US14219112

申请日：2014-03-19

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

IPC: F02C1/06 ,  F02K3/00 ,  F02C7/36 ,  F01D25/16 ,  F02K3/04 ,  F02C7/06

CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/00 ,  F02K3/04 ,  Y02T50/671 ,  Y10T29/4932

Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

Abstract translation: 燃气涡轮发动机包括壳体，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。 入口箱内设有齿轮架构。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 轴提供旋转轴。 轮毂由轴可操作地支撑。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。

公开(公告)号：US20150330306A1

公开(公告)日：2015-11-19

申请号：US14652840

申请日：2013-06-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/20 ,  F02C7/12 ,  F02C7/32 ,  F01D25/16

CPC classification number: F01D25/162 ,  F02C7/12 ,  F02C7/20 ,  F02C7/32 ,  F05D2220/325 ,  F05D2260/60 ,  Y02T50/675

Abstract: A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.

Abstract translation: 燃气涡轮发动机具有涡轮部分和封闭涡轮部分的壳体，其中安装结构固定到壳体以用于安装并且包括用于将空气输送到远程位置的内部流动通道。

公开(公告)号：US20150330300A1

公开(公告)日：2015-11-19

申请号：US14142965

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F02C3/10 ,  F02C7/27

CPC classification number: F02C3/10 ,  F02C7/27 ,  F02C7/275 ,  F02C7/32 ,  F02K3/06 ,  F05D2250/314

Abstract: A gas turbine engine has a first spool, a second spool, and a one-way clutch connecting the first and second spools. The one-way clutch disengages from the second spool when the first and second spools rotate at a predetermined speed.

Abstract translation: 燃气涡轮发动机具有第一阀芯，第二阀芯和连接第一阀芯和第二阀芯的单向离合器。 当第一和第二卷轴以预定速度旋转时，单向离合器与第二卷轴分离。

公开(公告)号：US20150300252A1

公开(公告)日：2015-10-22

申请号：US14753474

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Hung Duong ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/00

CPC classification number: F02C7/00 ,  F02C7/32 ,  F02C7/36 ,  F05D2230/70 ,  F05D2250/312 ,  F16H1/20 ,  Y10T29/49464

Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis.

Abstract translation: 用于燃气涡轮发动机的附件系统包括限定附件齿轮箱轴线并包括第一和第二侧面的附件齿轮箱。 第一齿轮箱包括可围绕垂直于附件齿轮箱的第一侧的轴线旋转的一个或多个轴，并且第二齿轮箱包括可围绕垂直于附件齿轮箱的第二侧的轴线旋转的一个或多个轴。 从动齿轮组限定输入轴并且驱动第一齿轮和第二齿轮组，绕相应于输入轴平行的第一和第二驱动轴。

公开(公告)号：US20150300187A1

公开(公告)日：2015-10-22

申请号：US14788345

申请日：2015-06-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Simon Pickford ,  William K. Ackermann ,  Nathan Snape

IPC: F01D9/06 ,  F01D5/02 ,  F01D1/02 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

Abstract translation: 示例性的涡轮机组件包括涡轮机的鼻锥，以及至少部分地在鼻锥内部的泵。 泵通过电动机选择性地旋转以将空气传送到内部。

公开(公告)号：US20150291289A1

公开(公告)日：2015-10-15

申请号：US14646752

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: B64D33/04 ,  B64C5/02 ,  F02K1/60 ,  B64D27/14

CPC classification number: B64D33/04 ,  B64C5/02 ,  B64D27/14 ,  B64D27/20 ,  F02K1/60

Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.

Abstract translation: 飞行器包括支撑在机身的后部的推进器。推力反向器安装在靠近推进系统的机身的后部，用于引导推进以减缓飞行器的方向。 推力反向器包括可围绕第一枢转轴线移动到展开位置的上部阻挡门，以及可围绕不平行于第一枢转轴线的第二枢转轴线移动的下部阻挡门。