公开(公告)号：US20150337675A1

公开(公告)日：2015-11-26

申请号：US14672561

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F02C7/25 ,  F01D17/00 ,  F02C5/12 ,  F01D25/24 ,  F01D25/14

CPC classification number: F01D11/14 ,  F01D11/24 ,  F01D17/00 ,  F01D25/145 ,  F01D25/24 ,  F02C5/12 ,  F02C7/25 ,  F05D2220/32 ,  F05D2260/231

Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

Abstract translation: 燃气涡轮发动机包括流体入口。 涡轮机部分包括涡轮机壳体。 防火墙位于涡轮机部分的上游。 导管构造成将流体从流体入口引导到涡轮壳体。 阀门位于与涡轮机部分相对的防火墙的第一侧上，并且构造成调节通过导管的流体的流动。

公开(公告)号：US20150315974A1

公开(公告)日：2015-11-05

申请号：US14649265

申请日：2013-05-29

Applicant: United Technologies Corporation

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

IPC: F02C9/00

CPC classification number: F02C9/00 ,  F01D13/006 ,  F01D13/02 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

Abstract: A gas turbine engine has a first shaft including a first compressor rotor. A second shaft includes a second compressor rotor disposed upstream of the first compressor rotor. The second compressor rotor has a first overall pressure ratio. The first compressor rotor has a second overall pressure ratio, with a ratio of the first overall pressure ratio to the second overall pressure ratio being greater than or equal to about 3.0.

Abstract translation: 燃气涡轮发动机具有包括第一压缩机转子的第一轴。 第二轴包括设置在第一压缩机转子的上游的第二压缩机转子。 第二压缩机转子具有第一总压力比。 第一压缩机转子具有第二总压力比，第一总压力比与第二总压力比的比率大于或等于约3.0。

公开(公告)号：US20150298794A1

公开(公告)日：2015-10-22

申请号：US14440753

申请日：2013-03-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C5/02 ,  B64D41/00

CPC classification number: B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D33/04 ,  B64D41/00 ,  F02K1/62

Abstract: An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser.

Abstract translation: 飞机包括支撑在机身后部的推进器。 靠近推进器支撑推力反向器，用于重定向推进，以降低飞机降落时的速度。 从机身的后部延伸的尾部从后部向前倾斜，并从推力反向器排出气流。

公开(公告)号：US20150292411A1

公开(公告)日：2015-10-15

申请号：US14440698

申请日：2013-03-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/20 ,  B64D27/20

CPC classification number: F02C7/20 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F05D2250/314

Abstract: A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.

Abstract translation: 用于飞行器的推进系统包括安装在飞行器的机身内的第一和第二涡轮发动机。 第一涡轮发动机包括驱动围绕第一推进轴设置的第一推进器的第一发动机芯。 第二涡轮发动机包括第二发动机芯和围绕平行于第一推进轴的第二推进轴设置的第二推进器。 第一发动机芯和第二发动机芯相对于第一和第二推进器轴线中的相应轴线成一定角度安装。

公开(公告)号：US20150292410A1

公开(公告)日：2015-10-15

申请号：US14443078

申请日：2013-06-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/18 ,  B64D2013/0603 ,  F01D25/12 ,  F02C6/08 ,  F02C9/18 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/327 ,  F05D2250/51 ,  Y02T50/675

Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.

Abstract translation: 燃气涡轮发动机具有要被输送到发动机的核心中的第一空气源和与第一空气源不同的第二气源，并且包括单独控制的第一和第二风扇，每个将空气输送到相应的第一和第 连接到不同辅助应用的第二导管。

公开(公告)号：US20150292408A1

公开(公告)日：2015-10-15

申请号：US14443145

申请日：2013-06-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/052 ,  B01D46/00

CPC classification number: F02C7/052 ,  B01D46/0023 ,  F02C7/12 ,  F05D2220/327 ,  F05D2260/40311 ,  F05D2260/607 ,  Y02T50/675

Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.

Abstract translation: 燃气涡轮发动机具有第一颗粒分离器台，其包括用于冲击空气流动通道的外周边处的空气的表面，捕获外周的冲击颗粒，并将捕获的颗粒向第二颗粒分离器台排出。 第一颗粒分离器台的内部空气朝向发动机的核心。 在第二颗粒分离器级上游的清洁空气用于除核心发动机以外的位置的空气功能。 颗粒排放设置在所述第二颗粒分离器台的下游。

公开(公告)号：US20150252730A1

公开(公告)日：2015-09-10

申请号：US14432377

申请日：2013-02-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/10

CPC classification number: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C7/20 ,  F02C7/32 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/672 ,  Y10T29/49321

Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

Abstract translation: 示例性燃气涡轮发动机包括至少包括风扇模块和风扇驱动涡轮机模块的推进器组件; 气体发生器组件，其至少包括压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮机; 以及由风扇驱动涡轮机模块驱动的用于旋转风扇模块的风扇的齿轮架构。 风扇模块和风扇驱动涡轮模块的重量小于燃气涡轮发动机总重量的约40％。

公开(公告)号：US20150121895A1

公开(公告)日：2015-05-07

申请号：US14187027

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

IPC: F02K1/32 ,  F02C3/04 ,  F02C7/20

CPC classification number: F02K1/605 ,  F01D25/24 ,  F02C3/04 ,  F02K1/60 ,  F02K1/62 ,  F02K1/625 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/14 ,  F05D2270/051

Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分。 燃气涡轮发动机还包括连接到前挂架并沿着后方向从第一环形部分延伸的轨道。 燃气涡轮发动机还包括第二环形部分，其布置在第一部分的后部并且联接到轨道。 第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成在关闭位置接合第一环形部分，从而提供对发动机芯的通路。 燃气涡轮发动机还包括布置在第二环形部分中的推力反向器。

公开(公告)号：US20150096303A1

公开(公告)日：2015-04-09

申请号：US14573003

申请日：2014-12-17

Applicant: United Technologies Corporation

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

IPC: F02C3/04 ,  F02C7/36

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/107 ,  F02K3/04 ,  F02K3/06

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

公开(公告)号：US20140294589A1

公开(公告)日：2014-10-02

申请号：US14302884

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/02

CPC classification number: F01D5/02 ,  F01D5/022 ,  F01D5/025 ,  F01D5/027 ,  F01D5/066 ,  F01D5/14 ,  F01D5/147 ,  F01D11/006 ,  F05D2240/20 ,  F05D2260/15 ,  Y10T29/49316 ,  Y10T29/4932

Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.

Abstract translation: 用于燃气涡轮发动机的线轴包括沿着旋转轴线限定的至少一个转子盘和沿着旋转轴线限定的至少一个转子环，转子环与转子盘接触。 转子盘和转子环形成轮廓以限定平滑的转子堆叠负载路径。