公开(公告)号：US20160102634A1

公开(公告)日：2016-04-14

申请号：US14639164

申请日：2015-03-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Daniel Bernard Kupratis

IPC: F02K3/04 ,  F02C7/057 ,  F02K1/00 ,  F02C3/06

CPC classification number: F02K3/04 ,  F01D13/003 ,  F01D13/006 ,  F02C3/06 ,  F02C7/36 ,  F02K1/52 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/4031

Abstract: A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.

Abstract translation: 旁路外壳接收风扇并限定前端。 气流路径将空气输送到旁路壳体的有限圆周范围内的入口管道中。 气流通过低压压缩机转子。 气流路径通过核心发动机，其包括高压压缩机转子，燃烧器和高压涡轮转子。 高压涡轮转子下游的燃烧产物进入中间管道，然后穿过低压涡轮转子。 低压涡轮转子比高压涡轮转子更靠近发动机前端。 低压涡轮转子轴向位于低压压缩机转子和风扇之间。 低压涡轮转子驱动风扇和低压涡轮转子。 还披露了一架飞机。

公开(公告)号：US20160097304A1

公开(公告)日：2016-04-07

申请号：US14966538

申请日：2015-12-11

Applicant: United Technologies Corporation

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

IPC: F01D25/28 ,  F01D25/16 ,  F01D17/10 ,  F01D25/24 ,  F01D5/06 ,  F01D15/12

CPC classification number: F01D25/28 ,  B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F01D1/02 ,  F01D5/02 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D17/105 ,  F01D17/14 ,  F01D17/16 ,  F01D25/162 ,  F01D25/24 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section. A gear arrangement is defined along an engine axis. The low spool is operable to drive the fan section through the gear arrangement. A mount system includes an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis.

Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括风扇部分和包括低压压缩机部分和低压涡轮机的低线轴。 高阀芯包括高压压缩机部分。 齿轮装置沿发动机轴线定义。 低阀芯可操作以通过齿轮装置驱动风扇部分。 安装系统包括后部安装件，其构造成使大致平行于发动机轴线的发动机壳体上的推力负载的至少一部分反作用。

公开(公告)号：US20160040594A1

公开(公告)日：2016-02-11

申请号：US14887433

申请日：2015-10-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F02C3/107 ,  F02C7/36

CPC classification number: F02C3/107 ,  F01D1/26 ,  F01D25/30 ,  F02C7/36 ,  F02K1/78 ,  F02K3/072 ,  F05D2250/36 ,  F05D2250/44 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine comprises a compressor section, a combustor section downstream of the compressor section, and a turbine section downstream of the combustor section. A mid-turbine frame includes an outer case portion and is configured to support the turbine section. At least one shaft defines an axis of rotation, and the turbine section comprises an inner rotor directly driving the shaft. The inner rotor includes an inner set of blades. An outer rotor is positioned immediately adjacent to the outer case portion and has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is positioned downstream of the combustor section, is mounted to the mid-turbine frame, and is coupled to the outer rotor to drive the at least one shaft.

Abstract translation: 燃气涡轮发动机包括压缩机部分，压缩机部分下游的燃烧器部分和燃烧器部分下游的涡轮部分。 中间涡轮机框架包括外壳部分并且构造成支撑涡轮部分。 至少一个轴限定了旋转轴线，并且涡轮部分包括直接驱动轴的内转子。 内转子包括内组叶片。 外转子定位成紧邻外壳部分并且具有与内组叶片分开的外组叶片。 外转子构造成围绕与内转子的旋转轴线相反的方向旋转。 齿轮系统设置在燃烧器部分的下游，安装到中间涡轮机框架，并且联接到外转子以驱动至少一个轴。

公开(公告)号：US20160032731A1

公开(公告)日：2016-02-04

申请号：US14799994

申请日：2015-07-15

Applicant: United Technologies Corporation

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

IPC: F01D5/18

CPC classification number: F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/288 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的转子包括可绕轴线旋转的转子盘和连接到转子盘的径向外侧的气体通道壁。 气体通道壁限定气体通道的径向向内部分。 多个转子轮辐径向地位于转子盘和气体通道壁之间。 多个转子轮辐在周向间隔开以限定转子盘和气体通道壁之间的多个冷却通道。 热屏障涂层设置在多个冷却通道中的至少一个的表面上。 还公开了一种冷却转子组件的方法。

公开(公告)号：US20160010554A1

公开(公告)日：2016-01-14

申请号：US14771055

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, 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 in communication with said mid-span pre-diffuser inlet and said combustor 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。 与所述中跨预扩散器入口和所述燃烧器部分连通的歧管。

公开(公告)号：US20160003149A1

公开(公告)日：2016-01-07

申请号：US14771069

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/14 ,  F01D9/04 ,  F01D5/02 ,  F02C3/04 ,  F02C7/04

Abstract: A gas turbine engine is provided comprising a compressor section, a combustor section, a diffuser case module, 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 compressor 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压缩机部分连通。

公开(公告)号：US20160003058A1

公开(公告)日：2016-01-07

申请号：US14755952

申请日：2015-06-30

Applicant: United Technologies Corporation

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

IPC: F01D5/22 ,  F01D5/02

CPC classification number: F01D5/225 ,  F01D5/02 ,  F01D5/10 ,  F01D5/34 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2260/941

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, adjacent ones of the plurality of blades are joined by a flexible web.

Abstract translation: 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，多个叶片中的相邻叶片通过柔性幅材连接。

公开(公告)号：US20150361900A1

公开(公告)日：2015-12-17

申请号：US14600101

申请日：2015-01-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/36 ,  F02C3/04

CPC classification number: F02C7/36 ,  F02C3/10

Abstract: A gas turbine engine comprises a gas generator rotating along a first axis of rotation, with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine rotates along a second axis of rotation, downstream of at least one gas generator turbine rotor. The fan drive turbine drives a pair of shaft portions extending in opposed directions beyond the axis of rotation of the gas generator.

Abstract translation: 燃气涡轮发动机包括沿着第一旋转轴线旋转的气体发生器，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。 风扇驱动涡轮沿第二旋转轴线旋转，在至少一个气体发生器涡轮机转子的下游。 风扇驱动涡轮驱动一对轴向部分，其延伸超过气体发生器的旋转轴线。

公开(公告)号：US20150337762A1

公开(公告)日：2015-11-26

申请号：US14284893

申请日：2014-05-22

Applicant: United Technologies Corporation

Inventor： Allan R. Penda ,  Gabriel L. Suciu ,  William G. Sheridan ,  Wesley K. Lord

IPC: F02K1/70 ,  F16H3/70 ,  F02C7/36

CPC classification number: F02K1/70 ,  F02C3/10 ,  F02C3/113 ,  F02C3/145 ,  F02C6/04 ,  F02C7/36 ,  F02K1/32 ,  F02K3/075 ,  F05D2260/40311 ,  F16H3/60 ,  Y02T50/671

Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

Abstract translation: 燃气涡轮发动机包括核心发动机，风扇，旁通管道和离合器。 风扇由核心发动机驱动。 旁路管道被配置为从风扇接收气流。 离合器连接核心发动机和风扇。 核心包括在一个实施例中的逆流双阀气体发生器。 在另一个实施例中，风扇由空气动力学地由核心发动机驱动的自由涡轮机驱动。 在一个实施例中，离合器包括倒档以反转风扇的旋转输出。 在一个实施例中，离合器和倒档传动装置实现在行星齿轮系统中。

公开(公告)号：US20150337738A1

公开(公告)日：2015-11-26

申请号：US14758277

申请日：2013-05-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

IPC: F02C9/18 ,  F02K3/02 ,  F02C7/12

CPC classification number: F02C7/12 ,  F02C3/13 ,  F02C3/145 ,  F02C6/04 ,  F02C6/08 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F05D2220/3217 ,  F05D2220/3218

Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.

Abstract translation: 在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。 第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。 空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。 空气混合系统从第一空气源和第二空气源接收空气。 第一空气源包括在第一压缩机转子的上游的第一压力下的空气。 第二空气源包括较低的第二压力的空气。 至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。