公开(公告)号：US20160097281A1

公开(公告)日：2016-04-07

申请号：US14855956

申请日：2015-09-16

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan

IPC: F01D1/04 ,  F01D5/12 ,  F01D9/04

CPC classification number: F01D1/04 ,  F01D5/12 ,  F01D5/26 ,  F01D9/04 ,  F01D25/04 ,  F04D29/542 ,  F04D29/666 ,  F04D29/668 ,  F05D2260/961 ,  Y02T50/673

Abstract: A circumferential airfoil array that provides a total airfoil count for the stage and that includes first and second sets of airfoils with different vibrational frequencies. First and second arcuate regions are arranged opposite one another and third and fourth arcuate regions are arranged opposite one another. The first set of airfoils has first primary, first secondary and first tertiary airfoil groups. The second set of airfoils has second primary, second secondary and second tertiary airfoil groups. The first primary airfoil group and second primary airfoil group are respectively arranged in the first and second arcuate regions. The first secondary airfoil group and second secondary airfoil group are arranged in the third arcuate region. The first tertiary airfoil group and the second tertiary airfoil group are arranged in the fourth arcuate region. The first and second arcuate regions provide greater than 50% of the total airfoil count.

Abstract translation: 圆周翼型阵列，其为舞台提供总翼型计数，并且包括具有不同振动频率的第一组和第二组翼型。 第一和第二弓形区域彼此相对地布置，并且第三和第四弓形区域彼此相对布置。 第一套翼型具有第一级主，第一级和第一级三级翼型组。 第二组翼型具有第二主，二次和二次三次翼型组。 第一主翼型组和第二主翼型组分别布置在第一和第二弓形区域中。 第一副翼面组和第二副翼组被布置在第三弧形区域中。 第一三次翼型组和第二三次翼型组布置在第四弧形区域中。 第一和第二弧形区域提供大于翼型总数的50％。

公开(公告)号：US20150369123A1

公开(公告)日：2015-12-24

申请号：US14745158

申请日：2015-06-19

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan

IPC: F02C3/107

CPC classification number: F02C3/107 ,  B23P6/002 ,  F01D5/026 ,  F01D5/066 ,  F02C3/10 ,  F05B2230/70 ,  F05B2230/80 ,  F05D2220/32 ,  F05D2230/51 ,  F05D2230/70 ,  F05D2230/80 ,  F05D2250/182 ,  F05D2260/30 ,  F05D2260/31 ,  Y10T29/4924

Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together faun a module that can be assembled, or disassembled, or both from the engine.

Abstract translation: 提供了一种用于组装和拆卸燃气涡轮发动机的模块的方法，以及被配置为用于模块化组装/拆卸的燃气涡轮发动机。 发动机包括第一轴和第二轴。 第一轴连接压缩机部分和第一涡轮部分。 第二轴连接到第二涡轮部分。 第一和第二轴可围绕发动机旋转轴线旋转。 第二轴和第二涡轮部分共同起动可以从发动机组装或拆卸的两个模块。

公开(公告)号：US20150354453A1

公开(公告)日：2015-12-10

申请号：US14707208

申请日：2015-05-08

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C7/05 ,  F02C3/04

CPC classification number: F02C7/05 ,  F05D2260/607 ,  Y02T50/675

Abstract: A gas turbine engine includes a core engine section which includes a compressor section and a core turbine section. The core engine is configured to rotate about a core axis. A drive turbine is configured to rotate about a drive turbine axis. A bypass passage connects an intake to the gas turbine engine directly with an exhaust of the drive turbine.

Abstract translation: 燃气涡轮发动机包括具有压缩机部和核心涡轮部的内燃机部。 核心引擎被配置为围绕芯轴旋转。 驱动涡轮机构造成围绕驱动涡轮机轴线旋转。 旁通通道将进气口直接与驱动涡轮机的排气连接到燃气涡轮发动机。

公开(公告)号：US20150330251A1

公开(公告)日：2015-11-19

申请号：US14707227

申请日：2015-05-08

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan

IPC: F01D25/16 ,  F01D1/18

CPC classification number: F01D25/162 ,  F01D1/18 ,  F01D25/164 ,  F01D25/20 ,  F16C19/26 ,  F16C27/045 ,  F16C2360/23

Abstract: A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal.

Abstract translation: 燃气涡轮发动机包括包括第一流体通道和可旋转轴的静态结构。 轴承组件相对于静态结构支撑可旋转轴。 轴承组件包括具有在静态结构和外圈之间延伸的阻尼通道的外座圈。 第二流体通道从阻尼器通道延伸到密封件。

公开(公告)号：US20200025067A1

公开(公告)日：2020-01-23

申请号：US16124863

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan

IPC: F02C3/107 ,  F02C3/10 ,  B23P6/00 ,  F01D5/02 ,  F01D5/06

Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.

公开(公告)号：US20180209350A1

公开(公告)日：2018-07-26

申请号：US15412102

申请日：2017-01-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02C7/36 ,  F02C9/26 ,  F02C9/20 ,  F02C3/10 ,  F04D27/00

CPC classification number: F02C7/36 ,  F02C3/10 ,  F02C3/113 ,  F02C9/20 ,  F02C9/26 ,  F02K3/06 ,  F04D27/002 ,  F05D2220/323 ,  F05D2260/40311 ,  F16H1/28

Abstract: A gas turbine engine comprises a fan rotor driven by a fan drive turbine, the fan drive turbine also rotating with one of a ring gear, an intermediate gear carrier, and a sun gear. A first compressor is driven by another of the ring gear, the intermediate gear carrier, and the sun gear. A second turbine rotates with the third of the ring gear, the intermediate gear carrier, and the sun gear.

公开(公告)号：US20170218844A1

公开(公告)日：2017-08-03

申请号：US15011762

申请日：2016-02-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul R. Hanrahan ,  Gabriel L. Suciu

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/22 ,  F02C7/32

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C6/08 ,  F02C7/12 ,  F02C7/32 ,  F02C9/22 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/232 ,  Y02T50/676

Abstract: A gas turbine engine has a main compressor section. A turbine section has a variable vane positioned upstream of a rotor blade, and the variable vane is provided with an actuator operable to control an orientation of the variable vane. A tap line taps air from the compressor section, and passes the tapped air through a cooling compressor. The cooling compressor is a fixed flow compressor. Air downstream of the cooling compressor is delivered into the turbine section.

公开(公告)号：US20170175632A1

公开(公告)日：2017-06-22

申请号：US14974779

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/10

CPC classification number: F02C7/185 ,  F01D25/162 ,  F02C3/10 ,  F02C6/08 ,  F02C7/12 ,  F02C7/125 ,  F02C7/141 ,  F02C7/18 ,  F02K3/06 ,  F05D2240/129 ,  F05D2250/51 ,  F05D2260/213 ,  Y02T50/676

Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

公开(公告)号：US20160237857A1

公开(公告)日：2016-08-18

申请号：US14625025

申请日：2015-02-18

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  George E. Allen ,  Christopher M. Juh

IPC: F01D25/28

CPC classification number: F01D25/285 ,  F01D5/026 ,  F05D2230/60 ,  F05D2230/70

Abstract: A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine includes a forward annular shaft defining an engine centerline axis. The system includes a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft. An aft annular shaft is radially inward from the forward annular shaft and aft of the ring. The ring is connected to a forward end of the aft annular shaft for common rotation therewith. The ring retains the aft annular shaft during disassembly. The system includes a stack nut axially held between an aft facing shoulder of the forward annular stub shaft and a forward facing surface of the ring to retain the stack nut during disassembly.

Abstract translation: 用于在拆卸燃气涡轮发动机的低压涡轮机期间维持燃气轮机中的轴承室的位置的系统包括限定发动机中心线轴线的正向环形轴。 该系统包括从前环形轴的内径表面径向向内并与其接合的环。 后环形轴从前环形轴和环的后部径向向内。 环连接到后环形轴的前端以与其共同旋转。 在拆卸过程中，环保留后端环形轴。 该系统包括轴向保持在前部环形短轴的前后肩部和环的前向表面之间的堆叠螺母，以在拆卸期间保持堆叠螺母。

公开(公告)号：US20160169102A1

公开(公告)日：2016-06-16

申请号：US14948991

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C3/14 ,  F02C3/107 ,  F02C7/12 ,  F02C3/06

CPC classification number: F02C3/145 ,  F02C3/06 ,  F02C3/107 ,  F02C7/12 ,  F02C7/143 ,  F02C7/36 ,  F02K3/06 ,  F02K3/115 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/211 ,  F05D2260/40311 ,  Y02T50/675

Abstract: A reverse flow gas turbine engine includes a propulsor section which includes a propulsor compressor section and a propulsor turbine section. The propulsor section includes a fan section and a geared architecture. The fan section is driven by the propulsor turbine section. A core section is arranged fluidly between the propulsor compressor section and the propulsor turbine section. The core section includes a reverse flow duct that reverses a core flow through the core section. At least one of the propulsor section and the core section has a two-spool arrangement.

Abstract translation: 逆流燃气涡轮发动机包括具有推进压缩机部分和推进涡轮部分的推进部分。 推进器部分包括风扇部分和齿轮架构。 风扇部分由推进涡轮机部分驱动。 在推进压缩机部分和推进涡轮机部分之间流体地设置有核心部分。 核心部分包括反向流动管道，其反转通过芯部分的芯流。 推进器段和芯部中的至少一个具有双线轴布置。