公开(公告)号：US20150345392A1

公开(公告)日：2015-12-03

申请号：US14821409

申请日：2015-08-07

Applicant: United Technologies Corporation

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

IPC: F02C7/06 ,  F02C3/04 ,  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 housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.

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。 转子连接到轮毂并支撑压缩机部分。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。 芯入口的径向内边界处于芯入口定子的位置，压缩机部分入口的径向内边界位于第一级低压压缩机转子的位置。

公开(公告)号：US20150300265A1

公开(公告)日：2015-10-22

申请号：US14440953

申请日：2013-02-20

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C7/36

CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/022 ,  F02C7/052 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/44 ,  F05D2260/20 ,  Y02T50/675

Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

Abstract translation: 燃气涡轮发动机包括外部机舱。 鼻锥在外部机舱的径向内侧间隔开。 鼻锥限定了用于引导外部空气流和内部空气流的颗粒分离器。 内部气流被引导通过压缩机的核心入口。 发动机还包括用于驱动至少一个螺旋桨的驱动齿轮系统。 可变桨距控制系统可以改变至少一个螺旋桨的桨距角。 一些外部气流被引导到驱动齿轮系统和俯仰控制系统中的至少一个。

公开(公告)号：US20150284067A1

公开(公告)日：2015-10-08

申请号：US14440995

申请日：2013-10-17

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C5/02 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26 ,  B64C5/06 ,  B64C9/02 ,  B64C19/00 ,  B64D27/14 ,  B64D33/04 ,  F02K1/56 ,  F02K1/78

Abstract: An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable.

Abstract translation: 飞机包括从机身延伸的尾巴。 尾部限定了具有支撑水平稳定器的第一和第二垂直稳定器的结构箱。 尾部包括至少一个牺牲控制表面和至少一个主控制表面。 在牺牲控制表面变得不可操作的情况下，主要控制面保持飞行器的可控性。

公开(公告)号：US20150267617A1

公开(公告)日：2015-09-24

申请号：US14729800

申请日：2015-06-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Allan R. Penda ,  Brian D. Merry ,  Christopher M. Dye ,  Nathan Snape

IPC: F02C7/18 ,  F02C7/14 ,  F02C7/08

CPC classification number: F02C7/185 ,  F02C7/08 ,  F02C7/14 ,  F02C7/18 ,  Y02T50/671

Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.

Abstract translation: 用于燃气涡轮发动机的热系统包括在交叉口处与旁路流动管道相交的旁通流动管道和压缩机流动管道。 阀位于交叉口内，并可在第一位置和第二位置之间移动。 第一位置可操作以选择性地使来自旁路流动管道的风扇旁路流动并且阻塞压缩机流动管道。 第二位置可操作以选择性地阻挡旁路流动管道并且连通通过压缩机流动管道的排出流。

公开(公告)号：US09121367B2

公开(公告)日：2015-09-01

申请号：US13869057

申请日：2013-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hasel Karl ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F01D1/00 ,  F02K3/02 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06

CPC classification number: F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。

公开(公告)号：US20150240745A1

公开(公告)日：2015-08-27

申请号：US14265856

申请日：2014-04-30

Applicant: United Technologies Corporation

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

IPC: F02K1/40 ,  F02C7/04 ,  F02C3/10 ,  F02C6/20

CPC classification number: F01D13/003 ,  F01D13/006 ,  F02K3/04 ,  F05D2250/314

Abstract: A propulsion system for an aircraft includes a furcated nozzle that has at least a first duct that extends from a first propulsor to a first trailing end duct opening and a second duct that extends from a second propulsor to a second trailing end duct opening.

Abstract translation: 用于飞行器的推进系统包括分叉喷嘴，其具有从第一推进器延伸到第一尾端管道开口的至少第一管道和从第二推进器延伸到第二后端管道开口的第二管道。

公开(公告)号：US20150226117A1

公开(公告)日：2015-08-13

申请号：US14597510

申请日：2015-01-15

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Michael E. McCune ,  Jesse M. Chandler ,  Alan H. Epstein ,  Steven M. O'Flarity ,  Christopher J. Hanlon ,  William F. Schneider ,  Joseph B. Staubach ,  James A. Kenyon

IPC: F02C3/107 ,  F02C9/18 ,  F02C3/067 ,  F02C3/06

CPC classification number: F02C3/107 ,  B64D27/18 ,  B64D35/04 ,  F01D13/003 ,  F02C3/06 ,  F02C3/067 ,  F02C7/36 ,  F02C9/18 ,  F02K3/077 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/40 ,  F05D2250/312

Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.

Abstract translation: 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。 风扇驱动涡轮机位于已经通过至少一个气体发生器涡轮机转子的燃烧产物的路径的下游。 风扇驱动涡轮机驱动轴并且轴接合齿轮以驱动至少三个风扇转子。

公开(公告)号：US20150211416A1

公开(公告)日：2015-07-30

申请号：US14595284

申请日：2015-01-13

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02C3/14 ,  F02C3/06 ,  F02C3/10 ,  F02C7/20 ,  F02C6/02

CPC classification number: F02C6/02 ,  F02C6/06 ,  F02K3/068 ,  F05D2250/314

Abstract: A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis. A fan drive turbine is on the engine central axis, downstream of the dual gas generators, and driven by output from the dual gas generators, to drive the fan.

Abstract translation: 燃气涡轮发动机包括发动机中心轴上的风扇。 多个气体发生器在风扇的下游，每个沿着相应的中心轴线相互偏移并且偏离发动机中心轴线。 风扇驱动涡轮机位于发动机中心轴上，位于双气体发生器的下游，并由双气体发生器的输出驱动，以驱动风扇。

公开(公告)号：US20150158597A1

公开(公告)日：2015-06-11

申请号：US14553793

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Wesley K. Lord

IPC: B64D41/00 ,  F02C3/107 ,  B64C11/30 ,  F02K3/075 ,  F01D21/14

CPC classification number: B64D41/007 ,  F02C7/32 ,  F02K3/06 ,  F05D2220/76 ,  F05D2260/70 ,  Y02T50/671

Abstract: A method of generating emergency power includes identifying a power-loss condition. In the power-loss condition, a desired quantity of power is determined Emergency power is generated from a turbofan section of the aircraft's engine. The turbofan has a plurality of blades, which have a variable pitch that can be adjusted as a function of the desired quantity of power and actual generated emergency power.

Abstract translation: 产生应急电力的方法包括识别功率损失状况。 在功率损失状态下，确定期望的功率量由紧急飞行器发动机的涡轮风扇段产生。 涡轮风扇具有多个叶片，其具有可根据期望的功率量和实际产生的应急功率调节的可变节距。

公开(公告)号：US20150113945A1

公开(公告)日：2015-04-30

申请号：US14512520

申请日：2014-10-13

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: F02K1/72 ,  F02K3/06 ,  F02K1/76 ,  F02K3/02

CPC classification number: F02K1/72 ,  F02K1/66 ,  F02K1/763 ,  F02K3/06 ,  F05B2250/314 ,  F05D2260/403

Abstract: A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.

Abstract translation: 一种燃气涡轮发动机，其具有径向围绕风扇轮毂的风扇壳体，以及可旋转地连接在风扇轮毂和风扇壳体之间的多个风扇出口导向叶片。 风扇部分还具有在壳体内的导向叶片的轴向上游的推力反向器开口。 燃气涡轮发动机也具有包含核心发动机的铁心壳。