公开(公告)号：US20160115865A1

公开(公告)日：2016-04-28

申请号：US14927567

申请日：2015-10-30

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C3/107 ,  F01D25/16 ,  F02K3/06

CPC classification number: F02C3/107 ,  F01D25/162 ,  F02K3/06 ,  F05D2260/4031

Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section, and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.

Abstract translation: 根据本公开的示例的燃气涡轮发动机的涡轮部分包括风扇驱动涡轮部分和第二涡轮部分。 风扇驱动涡轮部分在第一出口处具有第一出口区域，并且构造成以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域，并且构造成以比第一速度快的第二速度旋转。

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：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：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：US09038366B2

公开(公告)日：2015-05-26

申请号：US14067354

申请日：2013-10-30

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/02 ,  F02C1/06 ,  F02C3/13 ,  F01D25/16 ,  F02K3/04 ,  F02C7/36 ,  F02C9/18 ,  F01D5/14

CPC classification number: F02C3/13 ,  F01D5/143 ,  F01D25/162 ,  F02C7/36 ,  F02C9/18 ,  F02K3/04 ,  Y02T50/673

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 flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

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路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

公开(公告)号：US20150125259A1

公开(公告)日：2015-05-07

申请号：US14187612

申请日：2014-02-24

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F01D7/02 ,  F02C7/36

CPC classification number: F02C7/36 ,  F02K3/06 ,  Y02T50/671

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括除了别的以外的风扇部分，其包括可围绕发动机轴线旋转的风扇，其中多个风扇叶片围绕风扇叶片轴线可旋转。 齿轮架构与风扇通信，并由涡轮机部分驱动。 风扇以第一速度旋转，并且涡轮部分以不同于第一速度的第二速度旋转，并且与风扇部分连通的固定区域风扇喷嘴。

公开(公告)号：US20150121838A1

公开(公告)日：2015-05-07

申请号：US14190175

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F02C6/02 ,  B64D29/06 ,  F02K1/54

CPC classification number: B64D29/06 ,  B64D27/20 ,  F01D13/003 ,  F02K1/52 ,  F02K1/54 ,  F02K1/60 ,  F02K1/64 ,  F05D2250/314

Abstract: A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.

Abstract translation: 联合燃气涡轮发动机的系统具有第一发动机，第一发动机具有第一推进器和第二发动机，第一发动机具有第一轴线，第一发动机机芯具有第二轴线，第二发动机具有带有第三轴线的第二推进器和具有第四轴线的第二发动机机芯 。 第一轴和第三轴彼此平行; 并且第二轴线和第四轴线彼此成角度。

公开(公告)号：US20140186158A1

公开(公告)日：2014-07-03

申请号：US14012773

申请日：2013-08-28

Applicant: United Technologies Corporation

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

IPC: F02C3/107 ,  F02C7/36

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 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 geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

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。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向地布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

公开(公告)号：US20140174056A1

公开(公告)日：2014-06-26

申请号：US14190429

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven M. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06

CPC classification number: F02K3/06 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

Abstract: A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan speed about the axis and driven by the low pressure turbine through the gear train. The fan speed is less than a speed of the low pressure turbine. A core is surrounded by a core nacelle defined about the axis. A fan nacelle i s mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).

Abstract translation: 燃气涡轮发动机包括沿轴线限定的齿轮系。 沿着轴的线轴驱动齿轮系并且包括低阶数低压涡轮机。 风扇可以围绕轴线以风扇转速旋转，并由低压涡轮机通过齿轮系驱动。 风扇转速小于低压汽轮机的转速。 一个核心围绕着围绕轴定义的核心机舱。 一个风扇机舱至少部分安装在核心机舱周围，以便为风扇旁路气流定义一个风扇旁路气流路径。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。