公开(公告)号：US20170096944A1

公开(公告)日：2017-04-06

申请号：US15379634

申请日：2016-12-15

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/16 ,  F02K3/06 ,  F01D5/06 ,  F16H57/04 ,  F04D19/02 ,  F04D29/32 ,  F01D9/04 ,  F01D25/16 ,  F16H1/48 ,  F02C3/04 ,  F01D25/18

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/041 ,  F01D25/162 ,  F01D25/18 ,  F01D25/20 ,  F02C3/04 ,  F02C3/06 ,  F02C3/062 ,  F02C3/107 ,  F02C7/06 ,  F02C7/16 ,  F02C7/32 ,  F02K3/06 ,  F04D19/02 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H1/48 ,  F16H57/0412 ,  F16H57/0486 ,  Y02T50/671

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

公开(公告)号：US20170002738A1

公开(公告)日：2017-01-05

申请号：US15112869

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan

IPC: F02C7/06 ,  F01D25/20 ,  F02K3/06

CPC classification number: F02C7/06 ,  F01D25/20 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.

Abstract translation: 燃气涡轮发动机包括风扇驱动涡轮机，风扇转子和由风扇驱动涡轮驱动的齿轮减速器，从而驱动齿轮结构。 主要的供油系统为齿轮减速器内的部件和辅助供油系统供油。 辅助油系统运行，以确保在主供油系统故障时，齿轮减速将在充足的时间内供应至少30秒的动力。

公开(公告)号：US20160377167A1

公开(公告)日：2016-12-29

申请号：US15132650

申请日：2016-04-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F16H57/08 ,  F02K3/02 ,  F16H1/28

Abstract: A gear system for a turbofan engine assembly includes a sun gear rotatable about an engine centerline, a non-rotatable ring gear, and a rotating carrier that drives a fan. A plurality of planet gears is intermeshed between the sun gear and the ring gear. A rolling element bearing assembly supports rotation of the planet gear on the carrier. The rolling element bearing assembly includes a rolling element between an inner race and an outer race separated by a cage. A first passage for lubricant through the planet gear. A second passage is in communication with the first passage for communicating lubricant through the inner race to an interface between the inner race and the cage. A geared turbofan engine is also disclosed.

Abstract translation: 用于涡轮风扇发动机组件的齿轮系统包括可围绕发动机中心线旋转的太阳齿轮，不可旋转的环形齿轮和驱动风扇的旋转载体。 多个行星齿轮啮合在太阳齿轮和齿圈之间。 滚动体轴承组件支撑行星齿轮在载体上的旋转。 滚动元件轴承组件包括在由内笼和外座圈之间隔开的内圈之间的滚动元件。 润滑剂通过行星齿轮的第一通道。 第二通道与第一通道连通，用于将润滑剂通过内圈连通到内圈和保持架之间的界面。 还公开了一种齿轮涡扇发动机。

公开(公告)号：US20160376984A1

公开(公告)日：2016-12-29

申请号：US15182909

申请日：2016-06-15

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C3/107 ,  F02K3/06 ,  F02C7/06

CPC classification number: F02C3/107 ,  F01D25/164 ,  F01D25/18 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2230/64 ,  F05D2240/35 ,  F05D2240/54 ,  F05D2240/60 ,  F05D2250/611 ,  F05D2260/40311 ,  F05D2260/602 ,  F05D2260/609 ,  F05D2260/98 ,  F16H1/2818 ,  F16H1/48 ,  Y02T50/671

Abstract: A geared turbofan engine includes a fan rotatable about an engine axis. A compressor section compresses air and delivers the compressed air to a combustor where the compressed air is mixed with fuel and ignited to drive a turbine section that in turn drives the fan and the compressor section. A gear system is driven by the turbine section for driving the fan at a speed different than the turbine section. The gear system includes a carrier attached to a fan shaft. A plurality of planet gears are supported within the carrier. Each of the plurality of planet gears includes a first row of gear teeth and a second row of gear teeth supported within the carrier. A sun gear is driven by a turbine section. The sun gear is in driving engagement with the plurality of planet gears. At least two separate ring gears circumscribe the plurality of planet gears. Each of the at least two ring gears are supported by a respective flexible ring gear mount that enables movement relative to an engine static structure. A fan drive gear system for a gas turbine engine is also disclosed.

Abstract translation: 齿轮涡扇发动机包括可围绕发动机轴线旋转的风扇。 压缩机部分压缩空气并将压缩空气输送到燃烧室，在该燃烧室中压缩空气与燃料混合并被点燃以驱动涡轮部分，涡轮部分依次驱动风扇和压缩机部分。 齿轮系由涡轮机部分驱动，以不同于涡轮部分的速度驱动风扇。 齿轮系统包括附接到风扇轴的载体。 多个行星齿轮支撑在载体内。 多个行星齿轮中的每一个包括第一排齿轮齿和支撑在载体内的第二排齿轮齿。 太阳齿轮由涡轮部分驱动。 太阳齿轮与多个行星齿轮驱动接合。 至少两个单独的环形齿轮限定多个行星齿轮。 所述至少两个环形齿轮中的每一个由相对于发动机静态结构运动的相应的柔性环形齿轮架支撑。 还公开了一种用于燃气涡轮发动机的风扇驱动齿轮系统。

公开(公告)号：US20160356218A1

公开(公告)日：2016-12-08

申请号：US14622383

申请日：2015-02-13

Applicant: United Technologies Corporation

Inventor： Daniel B. Kupratis ,  William G. Sheridan

IPC: F02C6/12 ,  F01D9/04 ,  F02C7/36 ,  F04D29/54 ,  F02C3/04 ,  F01D5/12 ,  F04D29/32

CPC classification number: F02C6/12 ,  F01D1/12 ,  F01D5/12 ,  F01D9/041 ,  F02C3/04 ,  F02C3/045 ,  F02C3/073 ,  F02C3/14 ,  F02C7/36 ,  F04D29/324 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/35

Abstract: A turbine engine is provided that includes a first rotor, a second rotor and a combustor section. The first rotor includes a first set of compressor blades. The second rotor is adjacent the first rotor. The second rotor includes a second set of compressor blades and a set of turbine blades respectively connected to the second set of compressor blades. The combustor section is configured to receive air compressed by the first and the second sets of compressor blades. The combustor section is also configured to provide combustion products to the set of turbine blades.

Abstract translation: 提供一种涡轮发动机，其包括第一转子，第二转子和燃烧器部分。 第一转子包括第一组压缩机叶片。 第二转子与第一转子相邻。 第二转子包括分别连接到第二组压缩机叶片的第二组压缩机叶片和一组涡轮叶片。 燃烧器部分构造成接收由​​第一组和第二组压缩机叶片压缩的空气。 燃烧器部分还构造成向燃气轮机组提供燃烧产物。

公开(公告)号：US20160326906A1

公开(公告)日：2016-11-10

申请号：US14704631

申请日：2015-05-05

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Gabriel L. Suciu

IPC: F01D25/12 ,  F01D25/18

CPC classification number: F01D25/12 ,  B64C11/14 ,  F01D25/18 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T50/676

Abstract: An oil cooling system is provided. The system may comprise an oil inlet, a manifold fluidly coupled to the oil inlet, and a support strut comprising internal tubing fluidly coupled to the manifold. A heat exchanger may be fluidly coupled to the internal tubing of the support strut. A nose cone may be disposed forward of the heat exchanger and configured to rotate about an axis. The heat exchanger may be radially inward from a portion of the nose cone. A gas turbine engine is also provided. The gas turbine engine may comprise an epicyclic gear system and fan mechanically coupled to the epicyclic gear system. The fan may be configured to rotate about an axis. A nose cone may be coupled to the fan and configured to rotate about the axis. A heat exchanger may be aft of the fan and in fluid communication with the epicyclic gear system.

Abstract translation: 提供油冷却系统。 该系统可以包括油入口，流体地联接到油入口的歧管和包括流体地联接到歧管的内部管的支撑支柱。 热交换器可以流体地联接到支撑支柱的内部管道。 鼻锥可以设置在热交换器的前方并且被配置为围绕轴线旋转。 热交换器可以从鼻锥的一部分径向向内。 还提供燃气涡轮发动机。 燃气涡轮发动机可以包括机械地联接到行星齿轮系统的行星齿轮系统和风扇。 风扇可以被配置为绕轴线旋转。 鼻锥可以联接到风扇并且构造成围绕轴线旋转。 热交换器可以是风扇的后部并且与行星齿轮系统流体连通。

公开(公告)号：US20160312696A1

公开(公告)日：2016-10-27

申请号：US15105135

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan

IPC: F02C3/113 ,  F02C7/06 ,  F02K3/06

CPC classification number: F02C3/113 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2240/35 ,  F05D2260/4031

Abstract: A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid communication with a combustor and a turbine is in fluid communication with the compressor section. A speed reduction device driven by the turbine section for rotating the fan about the axis is mounted forward of the bearing assembly supporting rotation of the hub.

Abstract translation: 所公开的燃气涡轮发动机包括风扇部分，该风扇部分包括支撑可围绕轴线旋转的多个风扇叶片的轮毂和支撑轮毂绕轴线旋转的轴承组件。 压缩机部分与燃烧器流体连通，涡轮与压缩机部分流体连通。 由涡轮部分驱动的用于围绕轴线旋转风扇的减速装置安装在支撑轮毂旋转的轴承组件的前方。

公开(公告)号：US20160298543A1

公开(公告)日：2016-10-13

申请号：US14685240

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William G. Sheridan

IPC: F02C7/14 ,  F01D25/20 ,  F02C7/18

Abstract: A lubricant circulation system and method of circulating lubricant in a gas turbine engine are disclosed. The lubricant circulation system includes a nose cone having an aperture communicating air to an interior space of the nose cone, a heat exchanger disposed in the interior space, and a lubricant circulation pathway contained within a forward portion of the gas turbine engine and configured to circulate lubricant through the heat exchanger.

Abstract translation: 公开了一种在燃气轮机中循环润滑剂的润滑剂循环系统和方法。 润滑剂循环系统包括鼻锥体，其具有将空气连通到鼻锥体的内部空间的孔口，设置在内部空间中的热交换器和容纳在燃气涡轮发动机的前部中并被配置为循环的润滑剂循环路径 润滑剂通过热交换器。

公开(公告)号：US20160281610A1

公开(公告)日：2016-09-29

申请号：US15181102

申请日：2016-06-13

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F02C3/107 ,  F02C3/06 ,  F16H1/28

CPC classification number: F02C7/32 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C3/113 ,  F02C7/00 ,  F02C7/36 ,  F05D2210/12 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/40 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/36

Abstract: A gas turbine engine includes an engine centerline longitudinal axis and a fan section including a fan with fan blades and rotatable about the engine centerline longitudinal axis. A low corrected fan tip speed less than about 1400 ft/sec and the low corrected fan tip speed is an actual fan tip speed determined at an ambient temperature divided by [(Tram° R)/(518.7° R)]0.5, where T represents the ambient temperature in degrees Rankine. A bypass ratio greater than about 11 and a speed reduction device having a gear system with a gear ratio and a plurality of bearing systems. A low and high speed spool including a low and high pressure turbine and a first and second shaft, respectively. The first and second shafts are concentric and mounted via at least one of the bearing systems for rotation about the engine centerline longitudinal axis and the first shaft is in communication with the fan through the speed reduction device and the low pressure turbine includes four stages.

Abstract translation: 燃气涡轮发动机包括发动机中心线纵向轴线和风扇部分，风扇部分包括具有风扇叶片的风扇并可围绕发动机中心线纵向轴线旋转。 小于约1400ft / sec的低校正风扇叶尖速度和低校正风扇叶尖速度是在环境温度除以[（Tram°R）/（518.7°R）] 0.5时确定的实际风扇叶尖速度，其中T 表示环境温度，以度兰为单位。 旁路比大于约11，减速装置具有齿轮系齿轮系和多个轴承系统。 分别包括低压和高压涡轮机以及第一和第二轴的低速和高速线轴。 第一和第二轴是同心的，并且经由至少一个轴承系统安装，用于围绕发动机中心线纵向轴线旋转，并且第一轴通过减速装置与风扇连通，低压涡轮机包括四个阶段。

公开(公告)号：US20160245184A1

公开(公告)日：2016-08-25

申请号：US14626534

申请日：2015-02-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02C3/04

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2220/36 ,  F05D2230/51 ,  F05D2230/52 ,  F05D2260/40311 ,  F05D2260/74

Abstract: A turbine engine is provided that includes a fan rotor, a first compressor rotor, a second compressor rotor, a third compressor rotor, a first turbine rotor, a second turbine rotor, a third turbine rotor and a gear train. The fan rotor and the first compressor rotor are connected to the first turbine rotor through the gear train. The second compressor rotor is connected to the second turbine rotor. The third compressor rotor is connected to the third turbine rotor.

Abstract translation: 提供一种涡轮发动机，其包括风扇转子，第一压缩机转子，第二压缩机转子，第三压缩机转子，第一涡轮机转子，第二涡轮机转子，第三涡轮转子和齿轮系。 风扇转子和第一压缩机转子通过齿轮系连接到第一涡轮转子。 第二压缩机转子连接到第二涡轮转子。 第三压缩机转子连接到第三涡轮转子。